[Federal Register Volume 70, Number 206 (Wednesday, October 26, 2005)]
[Rules and Regulations]
[Pages 61727-61729]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21293]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20692; Directorate Identifier 2004-NM-229-AD; 
Amendment 39-14350; AD 2005-22-06]
RIN 2120-AA64


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

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This AD 
requires doing a one-time high-frequency eddy current inspection and 
repetitive detailed inspections for cracks in the frame web of main 
entry door number 1; and repairing the door frame web if necessary. 
This AD also provides for optional terminating action for the 
repetitive inspections. This AD is prompted by reports of cracking at 
the upper aft corner of the cutout for main entry door number 1 in the 
station 488 frame web. We are issuing this AD to detect and correct 
cracks in the frame web. These cracks could cause the frame to break 
and lead to rapid decompression of the airplane.

DATES: This AD becomes effective November 30, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of 
November 30, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
http://dms.dot.gov, or 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 U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20692; the directorate 
identifier for this docket is 2004-NM-229-AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 
747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series 
airplanes. That action, published in the Federal Register on March 23, 
2005 (70 FR 14589), proposed to require doing a one-time high-frequency 
eddy current inspection and repetitive detailed inspections for cracks 
in the frame web of main entry door number 1; and repairing the door 
frame web if necessary. That action also proposed to provide for 
optional terminating action for the repetitive inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Request To Include Optional Inspection

    One commenter requests that we include an option for Group 3 
airplanes in paragraph (f) of the proposed AD to perform an open-hole 
high-frequency eddy current (HFEC) inspection every 3,000 flight cycles 
instead of a detailed inspection every 1,500 flight cycles. The 
commenter states that the manufacturer has found this optional 
inspection to be structurally acceptable.
    We agree with the commenter that performing an HFEC inspection 
every 3,000 flight cycles would provide an equivalent level of safety 
as intended by this AD. However, the repetitive detailed inspection 
requirement is actually specified in paragraph (g) of the proposed AD, 
not paragraph (f). Therefore, we have revised paragraph (g) of the 
final rule, for Group 3 airplanes only, to include an option to perform 
a surface HFEC inspection of the frame web between the upper door sill 
and door stop number 8 for cracks every 3,000 flight cycles in 
accordance with the method referenced in Figure 3 or Figure 4 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin (ASB) 747-
53A2508, dated August 19, 2004.

Request To Revise Frame Inner Chord Inspection Requirement

    One commenter requests that we delete paragraph (j) of the proposed 
AD or revise it to state that when the frame inner chord is being 
replaced concurrently with the required frame web repairs, the open-
hole HFEC inspection of the frame inner chord is not required. The 
commenter states that the intent of paragraph (j) should be that when 
the frame inner chord is being replaced, there is no need to inspect 
the existing fastener holes in the chord because the chord is a new 
part. The commenter refers to the applicable Boeing Structural Repair 
Manual (SRM) and Boeing ASB 747-53A2508 to support this contention.
    We agree with this request. Open-hole HFEC inspection of the frame 
inner chord is a conditional inspection included in the repair 
procedures specified in paragraph (h) of this AD. However, AD 91-11-01, 
amendment 39-6997 (dated May 15, 1991), referenced in paragraph (j) of 
the proposed AD, only requires inspecting the frame inner chord, while 
AD 90-06-06, amendment 39-6490 (dated March 7, 1990), actually requires 
replacing the frame inner chord. Therefore, we have concluded that 
paragraph (j) of the proposed AD should have referred to AD 90-06-06, 
rather than AD 91-11-01, regarding concurrent replacement of the frame 
inner chord. We have revised paragraph (j) of the final rule to reflect 
the commenter's request and to correctly refer to AD 90-06-06. Further, 
to ensure that there is no confusion about the HFEC inspection, we also 
revised paragraph (h) of the final rule to include a reference to an 
``open-hole'' HFEC inspection.

Request To Clarify Use of Structural Repair Manual

    The same commenter requests that paragraph (h) of the proposed AD 
be clarified. The commenter asserts that paragraph (h) should be 
revised to state that the Boeing SRM meets the intent of the proposed 
AD. Further, the commenter requests that we clarify the statement ``For 
a repair method to be approved, the approval must specifically 
reference this AD.'' The commenter feels that paragraph (h) as written 
might lead to confusion.
    We agree with the commenter that the Boeing SRM procedures 
specified in the

[[Page 61728]]

service bulletin are appropriate sources of service information for the 
required repairs. We also agree with the commenter that the statement 
``For a repair method to be approved, the approval must specifically 
reference this AD'' applies only when the service bulletin advises the 
operators to contact Boeing for repair procedures, because that 
statement relates only to damage that is not addressed by the SRM 
repair procedures. To make it clear that any repair that is done in 
accordance with the SRM requires no further FAA approval, we have added 
Note 1 after paragraph (h) of the final rule, which states that the 
service bulletin ``references the Boeing structural repair manual as an 
additional source of service information to comply with the intent of 
paragraph (h) this AD.''

Related Rulemaking

    We have determined that certain detailed inspections required by 
paragraph (f) of AD 2005-20-30, amendment 39-14327 (70 FR 59252, 
October 12, 2005), or paragraph (f) of AD 2005-08-01, amendment 39-
14053 (70 FR 18290, April 11, 2005), are considered acceptable for 
accomplishing the repetitive detailed inspections required for Group 1 
and Group 2 airplanes by paragraph (g)(1) of this AD or for Group 3 
airplanes by paragraph (g)(2)(i) of this AD. Therefore, to give credit 
for accomplishing the corresponding actions described in AD 2005-20-30 
and AD 2005-08-01, we have retitled and reidentified paragraph (j) as 
paragraph (j)(1), and inserted new paragraph (j)(2) in the final rule.

Explanation of Editorial Corrections to Proposed AD

    We have made certain minor changes to punctuation, spelling and 
other mechanical elements of the proposed AD. These changes do not 
affect the technical content of the final rule.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Explanation of Change Made to This AD

    We have simplified paragraph (h) of this AD by referring to the 
``Alternative Methods of Compliance (AMOCs)'' paragraph of this AD for 
repair methods.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 274 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 140 airplanes of U.S. 
registry. The following table, using an estimated labor rate of $65 per 
work hour, provides the estimated costs for U.S. operators to comply 
with this AD.

----------------------------------------------------------------------------------------------------------------
                                       Number of
              Airplanes                airplanes    Work hours     Cost per airplane            Fleet cost
----------------------------------------------------------------------------------------------------------------
Group 1 (left and right side HFEC             119            2  $130...................  $15,470.
 inspection).
Group 1 (left and right side                  119            2  130, per inspection      15,470, per inspection
 detailed inspection).                                           cycle.                   cycle.
Group 2 (left side HFEC inspection).           16            1  65.....................  1,040.
Group 2 (left side detailed                    16            1  65, per inspection       1,040, per inspection
 inspection).                                                    cycle.                   cycle.
Group 3 (left and right side HFEC               5            2  130....................  650.
 inspection).
Group 3 (left and right side                    5            2  130, per inspection      650, per inspection
 detailed inspection).                                           cycle.                   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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-22-06 Boeing: Amendment 39-14350. Docket No. FAA-2005-20692; 
Directorate Identifier 2004-NM-229-AD.

[[Page 61729]]

Effective Date

    (a) This AD becomes effective November 30, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin 747-53A2508, dated August 19, 2004.

Unsafe Condition

    (d) This AD was prompted by reports of cracking at the upper aft 
corner of the cutout for main entry door number 1 in the station 488 
frame web. We are issuing this AD to detect and correct cracks in 
the frame web. These cracks could cause the frame to break and lead 
to rapid decompression 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.

Initial Inspections

    (f) Before the accumulation of 16,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later, do a high frequency eddy current (HFEC) 
inspection and a detailed inspection of the station 488 frame web, 
by doing all of the actions specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin (ASB) 747-53A2508, 
dated August 19, 2004; except as provided by paragraph (h) or (j) of 
this AD.

Repetitive Inspections

    (g) If no crack is found during the inspections required by 
paragraph (f) of this AD, do the applicable actions specified in 
paragraph (g)(1) or (g)(2) of this AD.
    (1) For airplanes identified in the service bulletin as Groups 1 
and 2: Repeat the detailed inspection required by paragraph (f) of 
this AD at intervals not to exceed 3,000 flight cycles.
    (2) For airplanes identified in the service bulletin as Group 3, 
do the actions specified in either paragraph (g)(2)(i) or (g)(2)(ii) 
of this AD.
    (i) Repeat the detailed inspection required by paragraph (f) of 
this AD thereafter at intervals not to exceed 1,500 flight cycles.
    (ii) Within 1,500 flight cycles after the inspections required 
by paragraph (f) of this AD, perform a HFEC inspection for cracks of 
the frame web between the upper door sill and door stop number 8 in 
accordance with the method referenced in Figure 3 or Figure 4 of the 
Accomplishment Instructions of the service bulletin. Repeat the HFEC 
inspection thereafter at intervals not to exceed 3,000 flight 
cycles.

Repairs

    (h) If any crack in the main entry door frame web is found 
during any inspection required by this AD: Before further flight, 
perform repairs--including an open-hole HFEC inspection of the frame 
inner chord--in accordance with the Accomplishment Instructions of 
Boeing ASB 747-53A2508, dated August 19, 2004. Where the service 
bulletin specifies to contact Boeing for appropriate action: Before 
further flight, repair the door frame web and any frame chord damage 
using a method approved in accordance with paragraph (k) of this AD.

    Note 1: Boeing ASB 747-53A2508, dated August 19, 2004, 
references the Boeing Structural Repair Manual as an additional 
source of service information to comply with the intent of paragraph 
(h) this AD.

Termination of Repeat Inspections

    (i) For the repaired frame web only, accomplishing the door 
frame web repair required by paragraph (h) of this AD ends the 
repetitive inspections required by paragraph (g) of this AD.

Credit for Actions Accomplished Using Alternative ADs

    (j)(1) If the frame inner chord replacement required by AD 90-
06-06, amendment 39-6490, (which identifies Boeing Service Bulletin 
747-53-2272, as listed in Boeing Document No. D6-35999, dated March 
31, 1989, as a source of service information) is accomplished 
concurrently with the repair of the station 488 door frame web 
specified by paragraph (h) of this AD, the open-hole HFEC inspection 
required by paragraph (h) of this AD is not required for the new 
frame inner chord.
    (2) Accomplishing the repetitive detailed inspections of the 
station 488 frame required by paragraph (f) of AD 2005-20-30, 
amendment 39-14327, or paragraph (f) of AD 2005-08-01, amendment 39-
14053, satisfies the requirements for the corresponding repetitive 
detailed inspections described by paragraphs (g)(1) and (g)(2)(i) of 
this AD, provided those inspections are performed at intervals 
corresponding with the applicable intervals required by this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(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 Commercial Airplanes DOA 
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) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (1) You must use Boeing Alert Service Bulletin 747-53A2508, 
dated August 19, 2004, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approves the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To 
get copies of the service information, contact Boeing Commercial 
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view 
the AD docket, go to the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 18, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-21293 Filed 10-25-05; 8:45 am]
BILLING CODE 4910-13-P