[Federal Register Volume 70, Number 70 (Wednesday, April 13, 2005)]
[Proposed Rules]
[Pages 19345-19351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-7380]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20917; Directorate Identifier 2004-NM-85-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -200B, -200F, -
200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes; 
and Model 747SR Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede two existing airworthiness 
directives (AD) for certain Boeing transport category airplanes. One AD 
currently requires doing certain inspections to detect cracks and 
corrosion around the lower bearing of the actuator attach fittings of 
the inboard and outboard flaps; repairing if necessary; and either 
overhauling the fittings or replacing them, which when done on certain 
actuator attach fittings ends the repetitive inspections. The other AD 
currently requires certain other inspections to detect discrepancies of 
the fittings of the flaps, and follow-on and corrective actions if 
necessary, which ends the repetitive inspections of the first AD. For 
certain airplanes, this proposed AD would require new inspections for 
discrepancies of the attach fittings of the flaps, and follow-on and 
corrective actions if necessary, which ends the repetitive inspections 
of both existing ADs. For all airplanes, this proposed AD would require 
repetitive overhaul/replacements of the fittings of both the inboard 
and outboard flaps. This proposed AD is prompted by reports of cracks 
of the attach fittings of the trailing edge flaps. We are proposing 
this AD to prevent cracking and other damage of the actuator attach 
fittings of the trailing edge flaps, which could result in abnormal 
operation or retraction of a trailing edge flap, and possible loss of 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by May 31, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide Rulemaking Web Site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this proposed AD 
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207.
    You may examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track

[[Page 19346]]

each action and assign a corresponding directorate identifier. The DMS 
AD docket number is in the form ``Docket No. FAA-2004-99999.'' The 
Transport Airplane Directorate identifier is in the form ``Directorate 
Identifier 2004-NM-999-AD.'' Each DMS AD docket also lists the 
directorate identifier (``Old Docket Number'') as a cross-reference for 
searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20917; 
Directorate Identifier 2004-NM-85-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You may examine the AD docket in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the DOT street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after the DMS 
receives them.

Discussion

    On June 20, 2001, we issued AD 2001-13-12, amendment 39-12292 (66 
FR 34526, June 29, 2001), for certain Boeing Model 747 series 
airplanes. That AD requires repetitive inspections to detect cracks and 
corrosion around the lower bearing of the actuator attach fittings of 
the inboard and outboard flaps. That AD also requires repetitive 
overhauls for certain actuator attach fittings or repetitive 
replacement of the fittings with new fittings, as applicable, which 
terminates the repetitive inspections. That AD also provides for 
replacement of actuator attach fittings with improved fittings, which 
terminates all requirements of that AD. That AD was prompted by reports 
of cracks on the lower bearing journal of the inboard actuator attach 
fittings of the outboard trailing edge flaps due to stress corrosion. 
We issued that AD to detect and correct cracking on the actuator attach 
fittings of the trailing edge flaps, which could result in abnormal 
operation or retraction of a trailing edge flap, and consequent reduced 
controllability of the airplane.
    On April 14, 2003, we issued AD 2003-08-11, amendment 39-13124 (68 
FR 19937, April 23, 2003), for all Boeing Model 747-100, -200B, -200F, 
-200C, -100B, -300, -100B SUD, -400, -400D, and -400F series airplanes; 
and Model 747SR series airplanes. That AD requires repetitive 
inspections to detect discrepancies of the actuator attach fittings of 
the inboard and outboard flaps, which are more comprehensive than those 
required by AD 2001-13-12, and follow-on and corrective actions as 
necessary. That AD was prompted by reports of three fractures of the 
attach fittings of the trailing edge flap actuator. We issued that AD 
to detect and correct cracking and other damage of the actuator attach 
fittings of the trailing edge flaps, which could result in abnormal 
operation or retraction of a trailing edge flap, and possible loss of 
controllability of the airplane.
    In the preamble of AD 2003-08-11, we indicated that the actions 
required by that AD were considered ``interim action,'' and that 
further rulemaking action was being considered to require repetitive 
replacement of the fittings with new or overhauled fittings. We now 
have determined that further rulemaking action is indeed necessary, and 
this proposed AD follows from that determination.

Relevant Service Information

    We have previously reviewed Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002 (cited in AD 2003-08-11 as the 
appropriate source of service information for the required actions). 
The service bulletin describes procedures for repetitive inspections of 
the attach fittings of the inboard and outboard flaps to detect 
discrepancies (i.e., Part 1). The inboard fittings are to be inspected 
using borescopic and detailed visual methods; and the outboard fittings 
are to be inspected using borescopic, detailed visual, and ultrasonic 
methods. The service bulletin also describes procedures for repetitive 
detailed visual (inboard and outboard flaps) and ultrasonic (outboard 
flap only) inspections with the attach fittings removed to detect 
discrepancies (i.e., Part 2). Discrepancies include surface corrosion, 
pitting, cracks, migrated or rotated bushings, and damaged or missing 
cadmium plating. The service bulletin also describes procedures for 
corrective and follow-on actions if necessary (i.e., Parts 3 through 
5), which includes repetitive detailed visual inspections to detect 
bushing migration and cracking and other damage of the actuator attach 
fittings; repetitive application of corrosion-inhibiting compound; and 
repetitive overhaul or replacement of any discrepant fitting with a new 
or overhauled fitting; as applicable. Repetitive overhauls of the 
attach fittings on the outboard and inboard flaps or repetitive 
replacements of those attach fittings with new or overhauled fittings 
(i.e., Part 5) ends the need for repetitive inspections.
    The manufacturer advises that Boeing Alert Service Bulletin 747-
57A2316 replaces Boeing Alert Service Bulletin 747-57A2310 (cited as 
the appropriate source of service information for the requirements of 
AD 2001-13-12). We have determined that accomplishing the actions 
specified in Boeing Service Bulletin 747-57A2316 will adequately 
address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing this AD, which 
would supersede ADs 2001-13-12 and 2003-08-11. This proposed AD would 
continue to require the following actions specified in AD 2001-13-12:
     Repetitive inspections to detect cracks and corrosion 
around the lower bearing of the actuator attach fittings of

[[Page 19347]]

the inboard and outboard flaps, and repair if necessary; and
     Repetitive overhauls of the actuator attach fittings on 
the outboard flaps and a one-time overhaul of the fittings on the 
inboard flaps, which ends the applicable repetitive inspections 
described previously; or repetitive replacements of the fittings on the 
inboard and outboard flaps with new fittings or a one-time replacement 
of those fittings with improved fittings, which ends the repetitive 
inspections described previously.
    In addition, this proposed AD would continue to require the 
following actions specified in AD 2003-08-11: Repetitive inspections to 
detect discrepancies of the actuator attach fittings of the inboard and 
outboard flaps (i.e., Part 1) and follow-on/corrective actions as 
necessary (i.e, Parts 2 and 5). Accomplishing the initial inspections 
(i.e., Part 1) would end the repetitive inspections around the lower 
bearing of the fittings of the inboard and outboard flaps described 
previously. This proposed AD would also require the actions specified 
in Parts 2 through 5 of Boeing Alert Service Bulletin 747-57A2316 
described previously, except as discussed under ``Difference Between 
the Proposed AD and the Service Bulletin.'' Accomplishing the actions 
in Part 2 of the service bulletin ends the inspections specified in 
Part 1 of the service bulletin. Accomplishing the actions in Part 5 of 
the service bulletin (i.e. repetitive overhauls or replacements of the 
attaching fittings at intervals not to exceed 8 years) ends all 
repetitive inspections for both inboard and outboard actuator attach 
fittings over eight years old. The compliance times are as follows:
     Part 1: 90 days (for inboard and outboard flaps);
     Part 2: 9 months (for inboard flaps), 18 months (for 
outboard flaps), and before further flight if any crack, corrosion, or 
damaged cad plating is found on either the inboard or outboard flap;
     Part 3: Repetitive intervals of 9 months (for inboard 
flaps only);
     Part 4: Repetitive intervals of 9 months (for outboard 
flaps only); and
     Part 5: Ranges from before the attach fitting is 8 years 
old, or within 2 years, whichever occurs first, to 3 years depending on 
the age of the outboard and inboard attach fittings. If any crack, 
corrosion, or damaged cad plating is found on either the inboard or 
outboard flap, the compliance time is before further flight.

Difference Between the Proposed AD and the Service Bulletin

    Boeing Alert Service Bulletin 747-57A2316 refers to ``detailed 
visual inspection'' for discrepancies of the actuator attach fittings 
of the inboard and outboard flaps. We have determined that the 
procedures in the service bulletin should be described as a ``detailed 
inspection.'' Note 1 has been included in this proposed AD to define 
this type of inspection.

Change to Existing ADs

    This proposed AD would retain all requirements of ADs 2001-13-12 
and 2003-08-11. Since those ADs were issued, the AD format has been 
revised, and certain paragraphs have been rearranged. As a result, the 
corresponding paragraph identifiers have changed in this proposed AD, 
as listed in the following two tables:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                            Corresponding requirement in
       Requirement in AD 2001-13-12               this proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (g)
paragraph (b).............................  paragraph (h)
paragraph (c).............................  paragraph (i)
paragraph (d).............................  paragraph (j)
paragraph (e).............................  paragraph (k)
paragraph (f).............................  paragraph (l)
------------------------------------------------------------------------


 
------------------------------------------------------------------------
                                            Corresponding requirement in
       Requirement in AD 2003-08-11               this proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (m)
paragraph (b).............................  paragraph (n)
paragraph (c).............................  paragraph (o)
paragraph (d).............................  paragraph (p)
------------------------------------------------------------------------

    We also have changed all references to a ``detailed visual 
inspection'' in the existing ADs to ``detailed inspection'' in this 
action. In addition, we have added a new requirement that, as of the 
effective date of this AD, the repetitive overhauls and replacements in 
paragraphs (j)(1) and (k)(1) of this proposed AD (paragraphs (d) and 
(e)(1) of AD 2001-13-12), respectively, must be done in accordance with 
Part 5 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2316, dated December 19, 2002, at intervals not to 
exceed 8 years. The repetitive intervals for those repetitive 
requirements in AD 2001-13-12 are 8 years or 8,000 flight cycles, 
whichever occurs first. Because corrosion is time dependant rather than 
flight-cycle dependant, we determined that the intervals for the 
repetitive overhauls and replacements should be based on time only. We 
also determined that operators should accomplish those actions in 
accordance with the latest service bulletin.

Costs of Compliance

    This proposed AD would affect about 1,000 Model 747-100, -200B, -
200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F series 
airplanes; and Model 747SR series airplanes worldwide. There are about 
181 airplanes on the U.S. registry. The average labor rate is $65 per 
hour. The following two tables provide the estimated costs for U.S. 
operators to comply with this proposed AD.

                                            Table 1.--Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                       Work
              Action                  hours            Parts            Cost per airplane        Fleet cost
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2001-           2  None.................  $130, per inspection  $23,530, per
 13-12).                                                               cycle.                inspection cycle.
Inspections specified in Part 1 of          2  None.................  $130 per inspection   $23,530 per
 the Accomplishment Instruction                                        cycle.                inspection cycle.
 (AI) of the referenced service
 bulletin (required by AD 2003-08-
 11).
Inspections specified in Part 2 of          5  None.................  $325 per inspection   $58,825 per
 the AI of the referenced service                                      cycle.                inspection cycle.
 bulletin (new proposed actions).
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[[Page 19348]]


                                            Table 2.--Estimated Costs
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                                           Work
                Action                    hours                 Parts                    Cost per airplane
----------------------------------------------------------------------------------------------------------------
Overhaul(s) as an alternative to the           37  None..........................  $2,405.
 replacement.
Replacement(s) as an alternative to             4  $6,623 (for the four attach     $6,883 (for the four attach
 the overhaul.                                      fittings on the outboard        fittings on the outboard
                                                    flaps) and $7,566 (for the      flaps) and $7,826 (for the
                                                    four attach fittings on the     four attach fittings on the
                                                    inboard flaps).                 inboard flaps), per
                                                                                    replacement cycle.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendments 39-12292 (66 
FR 34526, June 29, 2001) and 39-13124 (68 FR 19937, April 23, 2003) and 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2005-20917; Directorate Identifier 2004-NM-
85-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by May 31, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-13-12, amendment 39-12292; and AD 
2003-08-11, amendment 39-13124.
    Applicability: (c) This AD applies to all Boeing Model 747-100, 
-200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F 
series airplanes; and Model 747SR series airplanes; certificated in 
any category.

Unsafe Condition

    (d) This AD was prompted by reports of cracks of the attach 
fittings of the trailing edge flaps. We are issuing this AD to 
prevent cracking and other damage of the actuator attach fittings of 
the trailing edge flaps, which could result in abnormal operation or 
retraction of a trailing edge flap, and possible loss of 
controllability of the airplane.
    Compliance: (e) You are responsible for having the actions 
required by this AD performed within the compliance times specified, 
unless the actions have already been done.

Requirements of AD 2001-13-12

Affected Airplanes

    (f) For Boeing Model 747 series airplanes, as listed in Boeing 
Service Bulletin 747-57A2310, Revision 2, dated February 22, 2001, 
do the actions required by paragraphs (g) through (l) of this AD, as 
applicable.

Actuator Attach Fittings That Have Not Been Overhauled or Replaced

    (g) For actuator attach fittings on the outboard flaps that have 
not been overhauled in accordance with revisions of Boeing 747 
Overhaul Manual (OHM) 57-52-55 dated prior to June 1, 1999, or 
replaced with a new fitting, prior to August 3, 2001 (the effective 
date of AD 2001-13-12); and for actuator attach fittings on the 
inboard flap actuators that have not been overhauled in accordance 
with revisions of OHM 57-52-35, dated prior to June 1, 1999, or 
replaced with a new fitting, prior to August 3, 2001: Accomplish the 
actions in paragraph (i), (j), or (k) of this AD at the later of the 
times specified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Prior to the accumulation of 8 years since date of 
manufacture or 8,000 total flight cycles, whichever occurs first.
    (2) Within 6 months after August 3, 2001.

Actuator Attach Fittings That Have Been Overhauled or Replaced

    (h) For actuator attach fittings on the outboard flaps that have 
been overhauled in accordance with revisions of OHM 57-52-55 dated 
prior to June 1, 1999, or replaced with a new fitting, prior to 
August 3, 2001; and for actuator attach fittings on the inboard flap 
actuators that have been overhauled in accordance with revisions of 
OHM 57-52-35 dated prior to June 1, 1999, or replaced with a new 
fitting, prior to August 3, 2001:
Accomplish the actions in paragraph (i), (j), or (k) of this AD at 
the later of the times specified in paragraphs (h)(1) and (h)(2) of 
this AD.
    (1) Within 8 years or 8,000 total flight cycles after the attach 
fitting was overhauled or replaced, whichever occurs first.
    (2) Within 6 months after August 3, 2001.

Inspections and Corrective Action

    (i) Perform a detailed inspection to detect corrosion around the 
lower bearing journal on the actuator attach fittings on the inboard 
and outboard flaps, and perform an ultrasonic inspection to detect 
cracks around the lower bearing journal of the actuator attach 
fittings on the outboard flaps, in accordance with Boeing Service 
Bulletin 747-57A2310, Revision 1, dated November

[[Page 19349]]

23, 1999; or Revision 2, dated February 22, 2001.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


    Note 2: Inspections, overhauls, and replacements accomplished in 
accordance with Boeing Alert Service Bulletin 747-57A2310, dated 
June 17, 1999, are acceptable for compliance with the requirements 
of paragraph (i) of this AD.

    (1) If no corrosion or cracks are detected, repeat the 
inspections required by paragraph (i) of this AD at intervals not to 
exceed 18 months. Within 5 years after the initial inspections 
required by paragraph (i) of this AD, accomplish the actions 
specified in paragraph (j) or (k) of this AD.
    (2) If any corrosion is detected, prior to further flight, 
remove the corrosion by accomplishing the actions of either 
paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
    (i) If corrosion is within the limits of the Boeing 747 OHM: 
Prior to further flight, accomplish the actions specified in 
paragraph (j) or (k) of this AD.
    (ii) If corrosion is not within the limits of the Boeing 747 
OHM: Prior to further flight, accomplish the actions specified in 
paragraph (k) or (l) of this AD.
    (3) If any crack is detected: Prior to further flight, 
accomplish the actions specified in paragraph (k) or (l) of this AD.

Overhaul

    (j) Do the actions as specified in paragraphs (j)(1) and (j)(2) 
of this AD in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-57A2310, Revision 1, dated November 23, 
1999; or Revision 2, dated February 22, 2001.
    (1) Overhaul the actuator attach fittings on the outboard flaps. 
Repeat the overhaul of actuators on the outboard flaps as specified 
in Part 2 of the Work Instructions of the service bulletin 
thereafter at intervals not to exceed 8 years or 8,000 flight 
cycles, whichever occurs first. As of the effective date of this AD, 
the repetitive overhauls must be done in accordance with Part 5 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2316, dated December 19, 2002, at intervals not to exceed 8 
years since last overhaul. Accomplishment of the overhaul of the 
actuator attach fittings on the outboard flaps constitutes 
terminating action for the repetitive inspection requirements of 
paragraph (i)(1) of this AD for outboard flaps.
    (2) Overhaul the actuator attach fittings on the inboard flaps. 
Accomplishment of the overhaul of the actuator attach fittings on 
the inboard flaps constitutes terminating action for the 
requirements of paragraphs (g) through (l) of this AD for the 
actuator attach fittings on the inboard flaps.

Replacement

    (k) Replace the actuator attach fittings on the inboard and 
outboard flaps in accordance with paragraph (k)(1) or (k)(2) of this 
AD.
    (1) Replace the actuator attach fittings on the inboard and 
outboard flaps with new attach fittings in accordance with ``Part 
3--Replacement'' of Boeing Service Bulletin 747-57A2310, Revision 1, 
dated November 23, 1999; or Revision 2, dated February 22, 2001. 
Accomplishment of this replacement constitutes terminating action 
for the repetitive inspections required by paragraph (i) of this AD 
for the replaced fitting. Within 8 years or 8,000 flight cycles 
following accomplishment of the replacement, whichever occurs first, 
repeat this replacement or accomplish the overhaul specified in 
paragraph (j) of this AD. As of the effective date of this AD, the 
repetitive replacements must be done in accordance with Part 5 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-57A2316, dated December 19, 2002, at intervals not to exceed 8 
years since last replacement.
    (2) Replace the actuator attach fittings on the inboard and 
outboard flaps with improved attach fittings in accordance with 
``Part 4--Terminating Action'' of Boeing Service Bulletin 747-
57A2310, Revision 2, dated February 22, 2001. If accomplished, this 
replacement with improved fittings terminates the requirements of 
paragraphs (g) through (l) of this AD for the replaced fitting.

    Note 3: Replacement of the actuator attach fittings on the 
inboard flaps with fittings that have been overhauled before the 
effective date of this AD, in accordance with Boeing OHM 57-52-35, 
Temporary Revision 57-8, dated June 10, 1999; Temporary Revision 57-
10, dated May 8, 2000; or Full Revision 57-10, dated July 1, 2000; 
constitutes terminating action for the requirements of paragraphs 
(g) through (l) of this AD for the actuator attach fittings on the 
inboard flaps.

Repair

    (l) During any inspection done in accordance with paragraph (i) 
of this AD, if corrosion is found that is outside the limits 
specified in the Boeing 747 OHM, or if any crack is detected: In 
lieu of replacement of the actuator attach fittings in accordance 
with paragraph (k) of this AD, repair the actuator attach fittings 
on the inboard and outboard flaps in accordance with a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or per data meeting the type certification basis of the 
airplane approved by a Boeing Company Designated Engineering 
Representative who has been authorized by the Manager, Seattle ACO, 
to make such findings. For a repair method to be approved by the 
Manager, Seattle ACO, as required by this paragraph, the Manager's 
approval letter must specifically reference this AD.

Requirements of AD 2003-08-11

Inspection: Inboard Flap Attach Fittings

    (m) Perform borescopic and detailed inspections to detect 
discrepancies of the inboard flap attach fittings, in accordance 
with Part 1 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-57A2316, dated December 19, 2002. Discrepancies 
include corrosion, pitting, and damaged or missing cadmium plating. 
Do the inspection at the applicable time specified in paragraph 
(m)(1) or (m)(2) of this AD.
    (1) If the age of the fittings can be determined: Inspect within 
14 years since the fittings were new or last overhauled, or within 
90 days after May 8, 2003 (the effective date of AD 2003-08-11), 
whichever occurs later.
    (2) If the age of the fittings cannot be determined: Inspect 
within 90 days after May 8, 2003.

    Note 4: The exceptions specified in flag note 4 of Figure 1 of 
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002, 
apply to the requirements of paragraphs (m) and (n) of this AD.

Inspection: Outboard Flap Attach Fittings

    (n) Perform borescopic, detailed, and ultrasonic inspections to 
detect discrepancies of the outboard flap attach fittings, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2316, dated December 19, 2002. 
Discrepancies include surface corrosion, pitting, damaged or missing 
cadmium plating, and cracks. Do the inspection at the applicable 
time specified in paragraph (n)(1) or (n)(2) of this AD.
    (1) If the age of the fittings can be determined: Inspect within 
8 years since the fittings were new or last overhauled, or within 90 
days May 8, 2003, whichever occurs later.
    (2) If the age of the fittings cannot be determined: Inspect 
within 90 days after May 8, 2003.

Follow-on Actions: No Discrepancies Found

    (o) If no discrepancy is found during any inspection required by 
paragraph (m) or (n) of this AD: Do the actions specified by either 
paragraph (o)(1) or paragraph (o)(2) of this AD.
    (1) Repeat the applicable inspections specified in paragraphs 
(m) and (n) of this AD at intervals not to exceed 9 months until the 
actions specified in paragraph (o)(2) of this AD have been 
accomplished.
    (2) Perform a detailed inspection of the fitting to detect 
cracks, corrosion, damaged cadmium plating, or bushing migration, in 
accordance with and at the time specified in Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Do the follow-on actions in 
accordance with Parts 3, 4, and 5 of the Accomplishment Instructions 
of the service bulletin at the times specified in Figure 1 of the 
service bulletin, as applicable. Accomplishment of these actions 
terminates the initial and repetitive inspection requirements of 
paragraphs (m), (n), and (o)(1) of this AD.

    Note 5: The exceptions specified in flag note 2 of Figure 1 of 
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002, 
apply to those requirements of paragraphs (o)(2) and (p) of this AD 
that are specified in Part 2 of the service bulletin.


[[Page 19350]]



Corrective/Follow-on Actions: Discrepancies Found

    (p) If any discrepancy is found during any inspection required 
by paragraph (m), (n), or (o) of this AD: Perform applicable 
corrective and follow-on actions at the time specified and in 
accordance with Figure 1 of Boeing Alert Service Bulletin 747-
57A2316, dated December 19, 2002. Before further flight: Replace any 
discrepant fitting in accordance with Part 5 of the Accomplishment 
Instructions of the service bulletin, and accomplish the follow-on 
actions for the other fittings common to that flap in accordance 
with Part 2 of the Accomplishment Instructions of the service 
bulletin. Replacement of a fitting terminates the initial and 
repetitive inspections--specified in paragraphs (m), (n), and (o) of 
this AD--for that fitting only.

Terminating Action for Certain Requirements

    (q) Accomplishment of the actions required by paragraphs (m) and 
(n) of this AD ends the requirements of paragraphs (g) through (k) 
of this AD, except for the repetitive overhauls and repetitive 
replacements required by paragraphs (j)(1) and (k)(1) of this AD, 
respectively.

New Actions Required by This AD

Inspections: Attach Fittings of the Inboard and Outboard Flaps

    (r) For airplanes on which the repetitive borescopic, detailed, 
or ultrasonic (as applicable) inspections required by paragraphs 
(m), (n), or (o)(1) of this AD are being done as of the effective 
date of this AD: Inspect as specified in Table 1 of this AD. 
Accomplishing these actions ends the initial and repetitive 
inspections required by paragraphs (m), (n), and (o)(1) of this AD.

                Table 1.--Inspections of Attach Fittings
------------------------------------------------------------------------
             Requirements                         Description
------------------------------------------------------------------------
(1) Compliance time..................  Except as provided by paragraph
                                        (u) of this AD, at the
                                        applicable time specified in
                                        Figure 1 of Boeing Alert Service
                                        Bulletin 747-57A2316, dated
                                        December 19, 2002.
(2) Area to inspect..................  The attach fittings of the
                                        inboard and outboard flaps.
(3) Type of inspection...............  Detailed inspection (inboard and
                                        outboard flaps) and ultrasonic
                                        inspection (outboard flaps
                                        only).
(4) Discrepancies to detect..........  Surface corrosion, pitting,
                                        cracks, migrated or rotated
                                        bushings, and damaged or missing
                                        cadmium plating.
(5) In accordance with...............  Part 2 of the Work Instructions
                                        of Boeing Alert Service Bulletin
                                        747-57A2316, dated December 19,
                                        2002.
------------------------------------------------------------------------

Follow-on Actions: No Discrepancies Detected

    (s) If no discrepancy is detected during any inspection required 
by paragraph (r) of this AD: Do the follow-on actions in accordance 
with Parts 3, 4, and 5, as applicable, of the Work Instructions of 
Boeing Alert Service Bulletin 747-57A2316, dated December 19, 2002, 
at the applicable times specified in Figure 1 of the service 
bulletin, except as provided by paragraph (u) of this AD.

Overhaul/Replacement and Follow-on/Corrective Actions: Discrepancies 
Detected

    (t) If any discrepancy is detected during any inspection 
required by paragraph (r) of this AD: Do the actions specified in 
Table 2 of this AD at the applicable times specified in Figures 1 
and 2 of the service bulletin, except as provided by paragraph (v) 
of this AD.

                      Table 2.--Discrepancies Found
------------------------------------------------------------------------
                                         In accordance with Boeing Alert
              Requirements                Service Bulletin 747-57A2316,
                                            dated December 19, 2002--
------------------------------------------------------------------------
(1) Overhaul or replace discrepant       Part 5 of Work Instructions.
 fitting with new fitting.
(2) Do the follow-on and corrective      Parts 2 and 5 of Work
 actions for the other fitting common     Instructions, as applicable.
 to that flap, except as specified in
 flag note 2 in Figure 1 of the service
 bulletin.
------------------------------------------------------------------------

Compliance Time Requirements

    (u) For the requirements of paragraph (r) of this AD: Where 
Figure 1 of Boeing Alert Service Bulletin 747-57A2316, dated 
December 19, 2002, states a compliance time ``after the original 
issue date of the service bulletin,'' this AD requires compliance 
within the applicable compliance time after the effective date of 
this AD.
    (v) For the requirements of paragraph (s) of this AD: Where 
Figure 1 of Boeing Alert Service Bulletin 747-57A2316, dated 
December 19, 2002, specifies to repeat the overhaul or replacement 
``every 8 years,'' this AD requires compliance at intervals not to 
exceed 8 years.

Repetitive Overhaul or Replacement

    (w) Except as provided in paragraph (x) of this AD, at the 
applicable time specified in paragraph (w)(1) or (w)(2) of this AD, 
overhaul the attach fittings on the outboard and inboard flaps or 
replace the attach fittings with new or overhauled fittings, in 
accordance with Part 5 of the Work Instructions of Boeing Alert 
Service Bulletin 747-57A2316, dated December 19, 2002. Repeat the 
overhaul or replacement thereafter at intervals not to exceed 8 
years.
    (1) If the age of the fittings can be determined: Overhaul or 
replace within 8 years since the fittings were new or last 
overhauled, or within 2 years after the effective date of this AD, 
whichever occurs later.
    (2) If the age of the fittings cannot be determined: Assume that 
the fittings are more than 14 years old, and overhaul or replace 
within 2 years after the effective date of this AD.
    (x) Accomplishing the repetitive overhauls required by paragraph 
(j)(1) or repetitive replacements required by paragraph (k)(1) of 
this AD is acceptable for compliance with the requirements of 
paragraph (w) of this AD.

Alternative Methods of Compliance (AMOCs)

    (y)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Seattle ACO, to make those findings. For a repair method to be 
approved, the repair must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.
    (3) AMOCs approved previously in accordance with AD 2001-13-12 
are approved as AMOCs with the actions required by paragraphs (g) 
through (l) of this AD, as applicable. However, AMOCs approved 
previously are not considered

[[Page 19351]]

terminating action for the repetitive overhauls or replacements 
requirements of this AD.
    (4) AMOCs approved previously in accordance with AD 2003-08-11 
are approved as AMOCs with the actions required by paragraphs (m) 
through (p) of this AD, as applicable.


    Issued in Renton, Washington, on April 6, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7380 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P