[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Proposed Rules]
[Pages 7052-7056]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-2575]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / 
Proposed Rules  

[[Page 7052]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20325; Directorate Identifier 2003-NM-129-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, 
-200B, -200C, -200F, and -300 Series Airplanes; and Model 747SP and 
747SR Series Airplanes; Equipped With Pratt & Whitney Model JT9D-3, and 
-7 Series Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing transport category airplanes listed above. This 
proposed AD would require repetitive inspections for cracks of the 
upper surface of the aft lower spar web of the inboard and outboard 
struts, as applicable; and repetitive inspections for cracks of the 
upper surface of the intermediate web bay of the aft lower spar. This 
proposed AD would also require repetitive inspections and torque checks 
of the bolts common to the aft lower spar chords and the fitting of the 
rear engine mount bulkhead for missing, loose, or fractured bolts, as 
applicable; and corrective action, if necessary. This proposed AD is 
prompted by reports of cracking in the aft lower spar web and reports 
of missing and fractured bolts. We are proposing this AD to detect and 
correct cracking of the aft lower spar web, and to prevent missing, 
loose, or fractured bolts common to the aft lower spar chords and the 
fitting of the rear engine mount bulkhead, which could result in the 
loss of the aft lower spar load path and reduced structural capability 
of the pylon, which may result in the separation of the engine from the 
airplane.

DATES: We must receive comments on this proposed AD by March 28, 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.
     By 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.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124-
2207.
    You can 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. This docket 
number is FAA-2005-20325; the directorate identifier for this docket is 
2003-NM-129-AD.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

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-2005-20325; 
Directorate Identifier 2003-NM-129-AD'' in the subject line 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 submitted 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 
that 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 can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can 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

    We have received several reports of cracking in the aft lower spar 
web on Boeing Model 747-200B series airplanes equipped with Pratt & 
Whitney Model JT9D-7 series engines. The cracking in the aft lower spar 
web is the result of fatigue and sonic induced vibration. We also 
received reports of missing or fractured bolts common to the aft lower 
spar chord and the fitting of the rear engine mount bulkhead on Model 
747-100 series airplanes. The missing and fractured bolts were found on 
strut No. 1, No. 3 and No. 4. The missing and fractured bolts are made 
of Maraging or H-11 steel and are subject to stress corrosion cracking. 
These conditions, if not corrected, could result in the loss of the aft 
lower spar load path and reduced structural capability of the pylon, 
which may result in the separation of the engine from the airplane.
    The subject area on Model 747-100 and -200B series airplanes 
equipped with Pratt & Whitney Model JT9D-3 series engines is identical 
to that on the

[[Page 7053]]

affected Model 747-100 and -200B series airplanes equipped with Pratt & 
Whitney Model JT9D-7 series engines. Therefore, those Model 747-100 and 
-200B series airplanes equipped with Pratt & Whitney Model JT9D-3 
series engines are subject to the unsafe condition revealed on the 
affected Model 747-100 and -200B series airplanes equipped with Pratt & 
Whitney Model JT9D-7 series engines.
    In addition, the subject area on Model 747-100B, -100B SUD, -200C, 
-200F, and -300 series airplanes, and Model 747SP and 747SR series 
airplanes, equipped with Pratt & Whitney Model JT9D-3 and -7 series 
engines, is identical to that on the affected Model 747-100 and -200B 
series airplanes equipped with Pratt & Whitney Model JT9D-3 and -7 
series engines. Therefore, those Model 747-100B, -100B SUD, -200C, -
200F, and -300 series airplanes; and Model 747SP and 747SR series 
airplanes equipped with Pratt & Whitney Model JT9D-3 and -7 series 
engines are subject to the unsafe condition revealed on the affected 
Model 747-100 and -200B series airplanes equipped with Pratt & Whitney 
Model JT9D-3 and -7 series engines.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-54A2212, dated 
May 1, 2003, which describes the following procedures:

1. Part 1--Web Inspection

    For certain airplanes, do initial and repetitive detailed visual 
inspections of the upper surface of the aft lower spar web on the 
inboard struts, and outboard struts as applicable, for cracks. Do 
repairs, if necessary, and/or do ``Part 4--Stiffener Addition.''

2. Part 2--Intermediate Web Bay Inspection

    For certain airplanes, do initial and repetitive detailed visual 
inspections of the upper surface of the intermediate web bay of the aft 
lower spar for cracks, do repairs if necessary, and/or do ``Part 5--
Intermediate Stiffener Addition.''

3. Part 3--Maraging or H-11 Steel Bolt Inspection

    For certain airplanes, do initial and repetitive detailed visual 
inspections and torque checks of the bolts common to the aft lower spar 
chords and the fitting of the rear engine mount bulkhead for missing, 
loose, or fractured bolts; and replace bolt with new bolt if necessary. 
Replacing the bolt in accordance with ``Part 3'' includes related 
investigative actions and corrective action. The related investigative 
actions include high frequency eddy current (HFEC) inspections for 
cracks of the chord, web, and fitting and detailed visual inspections 
for corrosion of the hole in the fitting of the rear engine mount 
bulkhead. The corrective action specifies contacting the manufacturer 
if any crack or corrosion is found.

4. Part 4--Stiffener Addition (Optional)

    For certain airplanes, install stiffeners for inboard and outboard 
struts as applicable, do related investigative actions, and do repairs 
if necessary. The related investigative actions include HFEC 
inspections for cracks of the hole and around the aft fasteners of the 
fitting of the rear engine mount bulkhead. ``Part 4--Stiffener 
Addition'' procedures will either extend the repetitive inspection 
interval or end the repetitive inspections of ``Part 1--Web 
Inspection.''

5. Part 5--Intermediate Stiffener Addition (Optional)

    For certain airplanes, installing stiffeners for inboard and 
outboard struts will end the repetitive inspections of ``Part 2--
Intermediate Web Bay Inspection.'' Boeing Alert Service Bulletin 747-
54A2212 refers to Boeing Service Bulletins 747-71-2188 and 747-54-2115, 
as additional sources of service information for accomplishment of the 
installation.

6. Part 6--Maraging or H-11 Steel Bolt Replacement

    For certain airplanes, replace all Maraging or H-11 steel bolts 
with new inconel bolts; do related investigative actions (includes HFEC 
inspections for cracks of the chord and web, the chord and the fitting 
of the rear engine mount bulkhead fitting and the pylon skin; and 
detailed visual inspections for corrosion of the pylon skin and the 
hole of the fitting of the rear engine mount bulkhead); and do 
corrective action (includes contacting the manufacturer if any crack, 
corrosion, or damage is found which cannot be removed within the 
oversize limit). Replacement of all bolts with new inconel bolts in 
accordance with ``Part 6--Maraging or H-11 Steel Bolt Replacement'' 
ends the repetitive inspections of ``Part 3--Maraging or H-11 Steel 
Bolt Inspection.''
    We have determined that accomplishing the actions specified in the 
service information 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 airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require the following actions:
     Repetitive inspections for cracks of the upper surface of 
the aft lower spar web on the inboard and outboard struts, as 
applicable.
     Repetitive inspections for cracks of the upper surface of 
the intermediate web bay of the aft lower spar, as applicable.
     Repetitive inspections and torque checks of the bolts 
common to the aft lower spar chords and the fitting of the rear engine 
mount bulkhead for missing, loose, or fractured bolts, as applicable.
     Corrective action, if necessary.
    The proposed AD would require you to use the service information 
described previously to do these actions, except as discussed under 
``Differences Between the Proposed AD and the Service Bulletins.''

Differences Between the Proposed AD and the Service Bulletins

    The following differences between the proposed AD and the service 
bulletins have been coordinated with the manufacturer:
    1. Operators should note that although Boeing Alert Service 
Bulletin 747-54A2212, dated May 1, 2003, specifies that operators may 
contact the manufacturer for additional instructions for certain 
repairs, this proposed AD would require operators to repair according 
to a method approved by the FAA, or according to data meeting the 
certification basis of the airplane approved by an Authorized 
Representative for the Boeing Delegation Option Authorization 
Organization who has been authorized by the FAA to make those findings.
    2. Operators should also note that where Boeing Alert Service 
Bulletin 747-54A2212, dated May 1, 2003, references ``service bulletin 
747-71-2188 Revision 1 or later releases,'' this proposed AD would 
require that operators refer to Boeing Service Bulletin 747-71-2188, 
Revision 1, dated January 17, 1986; or Revision 2, dated September 24, 
1988. When referencing a specific service bulletin in an AD, using the 
phrase, ``or later FAA-approved revisions,'' violates Office of the 
Federal Register regulations for approving materials that are 
incorporated by reference.
    3. Operators should also note, that where the referenced Boeing 
Service

[[Page 7054]]

Bulletins 747-71-2188, Revision 1, dated January 17, 1986, and Revision 
2, dated September 24, 1988; and Boeing Service Bulletins 747-54-2115, 
dated February 14, 1986, and Revision 1, dated May 12, 1988; specify to 
repair according to an operators equivalent procedure, this proposed AD 
would require operators to repair according to a method approved by the 
FAA, or according to data meeting the certification basis of the 
airplane approved by an Authorized Representative for the Boeing 
Delegation Option Authorization Organization who has been authorized by 
the FAA to make those findings.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003, is 
referred to as a ``detailed inspection.'' We have included the 
definition for a detailed inspection in a note in the proposed AD.

Costs of Compliance

    There are about 244 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 82 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
  Applicable airplanes identified in                                               Average labor   airplane, per
  Boeing alert service bulletin 747-             Action             Work hours     rate per hour    inspection
             54A2212 as--                                                                              cycle
----------------------------------------------------------------------------------------------------------------
Groups 1-6............................  Web Inspection..........               8             $65            $520
Groups 7-8............................  Web Inspection..........               4              65             260
Groups 1-5............................  Web Bay Inspection......               4              65             260
Groups 1-6............................  Bolt Inspection.........               4              65             260
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated 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 
proposed AD.

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 adding the following new 
airworthiness directive (AD):

Boeing: Docket No. FAA-2005-20325; Directorate Identifier 2003-NM-
129-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by March 28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, -100B, -100B SUD, -
200B, -200C, -200F, and -300 series airplanes, and Model 747SP and 
747SR series airplanes; certificated in any category; equipped with 
Pratt & Whitney Model JT9D-3 and -7 series engines; as identified in 
Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003.

Unsafe Condition

    (d) This AD was prompted by reports of cracking in the aft lower 
spar web and reports of missing and fractured bolts. We are issuing 
this AD to detect and correct cracking of the aft lower spar web and 
to prevent missing, loose, or fractured bolts common to the aft 
lower spar chords and the fitting of the rear engine mount bulkhead, 
which could result in the loss of the aft lower spar load path and 
reduced structural capability of the pylon, which may result in the 
separation of the engine from 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.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means 
Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003.

Part 1--Web Inspections

    (g) At the applicable times specified in paragraph (g)(1), 
(g)(2), or (g)(3) of Table 1 of this AD, do initial and repetitive 
detailed inspections for cracks of the upper surface of the aft 
lower spar web of the inboard and outboard struts, as applicable; 
and before further flight, do any applicable repair; by doing all 
the actions specified in ``Part 1--Web Inspection'' of the Work 
Instructions of the service bulletin. For certain airplanes, the 
repetitive inspections may be deferred or ended provided that the 
optional stiffener addition specified in paragraph (k) of this AD is 
done.

    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

[[Page 7055]]

irregularity. Available lighting is normally supplemented with a 
direct source of good lighting at an intensity deemed appropriate. 
Inspection aids such as mirrors, magnifying lenses, etc. may be 
necessary. Surface cleaning and elaborate procedures may be 
required.''


              Table 1.--Compliance Times for Web Inspection
------------------------------------------------------------------------
                                  Initial Compliance
 For Airplanes Identified in the       Time Is--          Repetitive
      Service Bulletin As--                              Interval Is--
------------------------------------------------------------------------
(1) Group 1 airplanes on which    Within 12 months    At intervals not
 the modification specified in     after the           to exceed 2,400
 Boeing Service Bulletin 747-54-   effective date of   flight cycles.
 2028, dated August 1, 1972, has   this AD.
 been done; and Group 2
 airplanes.
(2) Group 1 airplanes on which    Within 6 months     At intervals not
 the modification specified in     after the           to exceed 350
 Boeing Service Bulletin 747-54-   effective date of   flight cycles.
 2028, dated August 1, 1972, has   this AD.
 not been done; and Group 7
 airplanes.
(3) Group 3, 4, 5, 6, and 8       Within 12 months    At intervals not
 airplanes.                        after the           to exceed 1,200
                                   effective date of   flight cycles.
                                   this AD.
------------------------------------------------------------------------

Part 2--Intermediate Web Bay Inspection

    (h) At the applicable times specified in paragraph (h)(1) or 
(h)(2) of Table 2 of this AD, do initial and repetitive detailed 
inspections for cracks of the upper surface of the intermediate web 
bay of the aft lower spar; and before further flight do any 
applicable repair; by doing all the actions specified in ``Part 2--
Intermediate Web Bay Inspection'' of the Work Instructions of the 
service bulletin. The repetitive inspections may be ended provided 
that the optional intermediate stiffener addition specified in 
paragraph (l) of this AD is done.

     Table 2.--Compliance Times for Intermediate Web Bay Inspections
------------------------------------------------------------------------
                                  Initial Compliance
 For Airplanes Identified in the       Time Is--          Repetitive
      Service Bulletin As--                              Interval Is--
------------------------------------------------------------------------
(1) Group 1 through 4 airplanes   Within 6 months     At intervals not
 on which the modification         after the           to exceed 350
 specified in Boeing Service       effective date of   flight cycles.
 Bulletin 747-71-2188, dated       this AD.
 March 14, 1983, has been done
 and on which the additional
 work specified in Boeing
 Service Bulletin AD 747-71-
 2188, Revision 1, dated January
 17, 1986; or Revision 2, dated
 September 24, 1988; has not
 been done.
(2) Group 5 airplanes on which    Within 6 months     At intervals not
 the modification specified in     after the           to exceed 350
 Boeing Service Bulletin 747-54-   effective date of   flight cycles.
 2115, dated February 14, 1986;    this AD.
 or Revision 1, dated May 12,
 1988; has not been done.
------------------------------------------------------------------------

Part 3--Maraging or H-11 Steel Bolt Inspection

    (i) For Group 1 through 6 airplanes identified in the service 
bulletin: Within 12 months after the effective date of this AD, do a 
detailed inspection and torque check of the bolts common to the aft 
lower spar chords and the fitting of the rear engine mount bulkhead 
for missing, loose, or fractured bolts, and do any applicable 
replacement (including related investigative actions and corrective 
action), by doing all the actions specified in ``Part 3 `` Maraging 
or H-11 Steel Bolt Inspection'' of the Work Instructions of the 
service bulletin, except as provided by paragraph (o) of this AD. Do 
any applicable replacements (including related investigative actions 
and corrective action) before further flight, except as provided by 
paragraph (j) of this AD. Repeat the actions thereafter at intervals 
not to exceed 18 months. The inspections and torque checks specified 
in paragraph (i) of this AD may be ended provided that the 
replacement specified in paragraph (n) of this AD is done.
    (j) If during any inspection required by paragraph (i) of this 
AD, one of the conditions specified in paragraphs (j)(1) and (j)(2) 
of this AD is found, do the applicable actions specified in 
paragraphs (j)(1) and (j)(2) of this AD.
    (1) If a missing or fractured bolt is found on the inboard strut 
in any one bay, within 36 months after replacing the bolt with a new 
bolt, do the replacement specified in paragraph (n) of this AD.
    (2) If two or more missing or fractured bolts are found in any 
one bay, before further flight, do the replacement specified in 
paragraph (n) of this AD.

Part 4--Optional Stiffener Addition

    (k) Except as provided by paragraph (o) of this AD, 
accomplishing the optional stiffener addition for the inboard and 
outboard struts, doing the related investigation actions, and doing 
any applicable repair, by doing all the actions specified in ``Part 
4--Stiffener Addition'' of the Work Instructions of the service 
bulletin before further flight after accomplishing the actions 
specified in paragraph (g) of this AD, defers or ends the repetitive 
inspections required by paragraph (g) of this AD as follows:
    (1) For airplanes listed in paragraph (g)(2) of Table 1 of this 
AD, accomplishing the optional stiffener addition extends the 
repetitive inspections required by paragraph (g) of this AD to 
intervals not to exceed 2,400 flight cycles.
    (2) For airplanes listed in paragraph (g)(3) of Table 1 of this 
AD, accomplishing the optional stiffener addition ends the 
repetitive inspections required by paragraph (g) of this AD.

Part 5--Optional Intermediate Stiffener Addition

    (l) For airplanes identified in paragraphs (h)(1) and (h)(2) of 
Table 2 of this AD: Accomplishing the optional intermediate 
stiffener addition for the inboard and outboard struts, by doing all 
the actions specified in ``Part 5--Intermediate Stiffener Addition'' 
of the Work Instructions of the service bulletin before further 
flight after accomplishing the actions specified in paragraph (h) of 
this AD, except as provided by paragraph (m) of this AD, ends the 
repetitive inspections required by paragraph (h) of this AD.
    (m) Where the service bulletin specifies to install stiffeners 
as shown in ``service bulletin 747-71-2188 Revision 1 or later 
releases (Group 1, 2,3, and 4 Airplanes) or 747-54-2115 Original 
Issue or Revision 1 (Group 5 Airplanes),'' this AD requires that 
those actions be done in accordance with Boeing Service Bulletin 
747-71-2188, Revision 1, dated January 17, 1986, or Revision 2, 
dated September 24, 1988; or Boeing Service Bulletin 747-54-2115, 
dated February 14, 1986, or Revision 1, dated May 12, 1988; as 
applicable, except as provided by paragraph (o) of this AD.

Part 6--Maraging or H-11 Steel Bolt Replacement

    (n) For Group 1 through 6 airplanes identified in the service 
bulletin: Except as provided by paragraph (o) of this AD, replacing 
all Maraging or H-11 steel bolts with new inconel bolts, doing the 
related investigation actions, and doing any applicable corrective 
action, by doing all the actions specified in ``Part 6--Maraging or 
H-11 Steel Bolt Replacement'' of the Work Instructions of the 
service bulletin ends the inspections and torque checks required by 
paragraph (i) of this AD.

[[Page 7056]]

Contact the FAA

    (o) If during any action required by this AD the service 
bulletin specifies to contact Boeing for additional instructions; or 
if Boeing Service Bulletin 747-71-2188, Revision 1, dated January 
17, 1986, or Revision 2, dated September 24, 1988; or Boeing Service 
Bulletin 747-54-2115, dated February 14, 1986, or Revision 1, dated 
May 12, 1988, specifies to repair according to operators equivalent 
procedures: Before further flight, repair according to a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or according to data meeting the certification basis of 
the airplane 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 approval must specifically reference this 
AD.

Parts Installation

    (p) As of the effective date of this AD, no person may install a 
Maraging or H-11 steel bolt in the locations specified in this AD, 
on any airplane.

Alternative Methods of Compliance (AMOCs)

    (q) 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.

    Issued in Renton, Washington, on January 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-2575 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P