AD 2002-16-11

[Federal Register Volume 67, Number 159 (Friday, August 16, 2002)]
[Rules and Regulations]
[Pages 53471-53473]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-20510]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-333-AD; Amendment 39-12850; AD 2002-16-11]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 777 series airplanes, that requires 
inspection of certain aft axle pivot pins of the main landing gear 
(MLG) for heat damage and either reworking of damaged pins or 
replacement of damaged pins with new or serviceable pins. This action 
is necessary to prevent breakage of the aft axle pivot pin of the MLG, 
which could overload the center axle, causing the tires to blow out 
upon landing, and could disengage the aft axle so that it jams the gear 
in the wheel well, preventing proper extension of the MLG. This action 
is intended to address the identified unsafe condition.

DATES: Effective September 20, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 20, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, PO Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Technical Information: Suzanne 
Masterson, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2772; fax (425) 227-1181.
    Other Information: Judy Golder, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4241, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: <a href="/cdn-cgi/l/email-protection#046e71607d2a636b68606176446265652a636b72"><span class="__cf_email__" data-cfemail="80eaf5e4f9aee7efece4e5f2c0e6e1e1aee7eff6">[email&#160;protected]</span></a>. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 777 series 
airplanes was published in the Federal Register on January 4, 2002 (67 
FR 541). That action proposed to require inspection of certain aft axle 
pivot pins of the main landing gear (MLG) for heat damage and either 
reworking of damaged pins or replacement of damaged pins with new pins.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Clarify Inspection Method

    One commenter requests that the FAA revise paragraph (a)(2) of the 
proposed AD because the description of one of the appropriate 
inspection methods as a ``magnetic particle inspection'' is incomplete. 
The commenter states that the term should be changed to ``metallurgical 
inspection.''
    We partially concur with the commenter's request. We acknowledge 
that the magnetic particle inspection is only one part of the 
inspection procedures described in Figure 2 of Boeing Special Attention 
Service Bulletin 777-32-0029, dated May 18, 2000. However, we find that 
the term ``metallurgical inspection'' is also not fully descriptive or 
inclusive of all of the steps in the inspection process. For 
clarification of the acceptable inspection methods, we have revised the 
wording of paragraph (a)(2) of this final rule to state that the 
required inspection ``must be done either by the Barkhausen Noise 
Inspection method for chromium-plated parts, or by following all of the 
procedures in Figure 2 of the service bulletin (including nital etching 
and a magnetic particle inspection), in accordance with the service 
bulletin.''

Allow Installation of Serviceable Pins

    One commenter requests that we revise paragraph (a)(2)(ii) of the 
proposed AD to allow installation of a serviceable aft axle pivot pin. 
The commenter states that this paragraph is confusing because it may be 
interpreted to allow installation only of the same aft axle pivot pin 
removed from the MLG or a new pin. The commenter would like to be 
allowed to remove the existing pin, and install either a new pin or a 
pin that has been inspected in accordance with the proposed AD.
    We concur that both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD 
need to be clarified as the commenter describes. It is not our 
intention to prohibit installation of a serviceable pin that has been 
inspected. Therefore, we have revised paragraphs (a)(2)(i) and 
(a)(2)(ii) of this final rule to allow installation of a new or 
serviceable aft axle pivot pin in the MLG. We have also revised the 
Summary section of this AD accordingly.

Extend Compliance Time for Follow-on Inspection of Pivot Pin

    One commenter requests that we extend the compliance time for the 
follow-on inspection for heat damage of any aft axle pivot pin with an 
EGL prefix, which would be required by paragraph (a)(1)(ii) of the 
proposed AD. The commenter states that operators should be allowed to 
remove and inspect the pins at the next maintenance opportunity, rather 
than ``prior to further flight,'' as long as the action is done within 
the 18-month compliance time.
    We concur that we need to clarify the compliance time for the 
follow-on removal and inspection of the aft axle pivot pin described in 
paragraph (a)(1)(ii) of this AD. Inspecting an affected aft axle pivot 
pin for heat damage within 18 months after the effective date of this 
AD is acceptable for compliance with this AD. We have revised paragraph 
(a)(1)(ii) of this AD to clarify our intent.

[[Page 53472]]

Clarify Paragraph (a)(1)

    One commenter suggests that we revise paragraph (a)(1) for 
clarification. The commenter states that an operator was confused by 
the applicability of that paragraph, ``For airplanes which have line 
numbers 1 through 68 inclusive (designated as Group 1 airplanes in the 
service bulletin) and on which the aft axle pivot pin of the MLG has 
been replaced prior to the effective date of this AD.'' The operator 
interpreted this as meaning that the paragraph applies to airplanes 
with line numbers (L/Ns) 1 through 68 and higher. The commenter 
suggests a comma after the parenthetical phrase. We concur and have 
revised paragraph (a)(1) accordingly.

Credit for Actions Accomplished Previously

    One commenter requests that we revise the proposed AD to provide 
credit for airplanes on which the actions in Boeing Special Attention 
Service Bulletin 777-32-0029 were accomplished before the effective 
date of the AD. The commenter notes that, in the service bulletin, the 
manufacturer recommends compliance within 18 months after service 
bulletin release. Thus, many operators have already done the 
inspections in the service bulletin. The commenter states that the 
wording of the proposed AD would require operators that have already 
complied with the proposed requirements to request an alternative 
method of compliance (AMOC).
    For similar reasons, the same commenter requests that we remove the 
airplane with L/N 1 from the applicability of this AD. The commenter 
points out that the ``Group 1'' inspection described in the service 
bulletin was accomplished on this airplane before it was delivered, and 
no subject aft axle pivot pin was found.
    We do not concur that any change is necessary. We give credit for 
actions accomplished before the effective date of an AD by means of the 
phrase ``Compliance: Required as indicated, unless accomplished 
previously,'' which appears in every AD. If an operator's maintenance 
records show conclusively that the aft axle pivot pin installed on an 
airplane has been inspected per the referenced service bulletin and 
found to be acceptable, no further action is required.
    Specifically with regard to the airplane with L/N 1, though that 
airplane may have been delivered with a pin that is not subject to this 
AD, it is possible that a subject pin could be installed on that 
airplane after delivery. Therefore, L/N 1 must be included in the 
applicability of this AD, so that it is subject to paragraph (b) of 
this AD, the ``Spares'' paragraph, which prohibits installation of a 
subject aft axle pivot pin unless it has been inspected per this AD.
    We have made no change to the final rule related to these requests.

Eliminate Inspection in Spares Provision

    One commenter requests that we eliminate the inspection specified 
in paragraph (b), the ``Spares'' paragraph, of the proposed AD. The 
commenter states that the proposed requirement would impose an 
unnecessary inspection on all aft axle pivot pins with an ``EGL'' 
prefix, rather than only the suspect pins. The commenter notes that 
Boeing Special Attention Service Bulletin 777-32-0029, dated May 18, 
2000, was issued to address a finite number of pins, which were 
manufactured between November 1996 and October 1999. The commenter 
states that the root cause of the defect in this set of pins was 
identified and the supplier has corrected its process accordingly. The 
commenter is concerned about forcing operators to inspect pins produced 
after the process was corrected in October 1999.
    Similarly, a second commenter requests that we revise paragraph (b) 
of this AD to exempt aft axle pivot pins purchased from the 
manufacturer after the release date of Boeing Special Attention Service 
Bulletin 777-32-0029. The commenter notes that pins purchased from the 
manufacturer after the release of the service bulletin should not be 
subject to the identified unsafe condition. The commenter indicates 
that the manufacturer has advised that it is not necessary to inspect 
such pins.
    We do not concur with these requests. While we have learned that 
the manufacturer is working to develop a method of tracking the subject 
pins, no such system is currently in place, so it is possible that some 
of the subject pins may have been procured as spares. Thus, we find it 
necessary to require inspection of any aft axle pivot pin having a 
serial number with the prefix ``EGL.'' If a system is in place to track 
the pins, operators may request approval of an alternative method of 
compliance in accordance with paragraph (c) of this AD. No change to 
the final rule is necessary in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, we have determined that air safety and the public interest 
require the adoption of the rule with the changes previously described. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Cost Impact

    There are approximately 263 Model 777 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 73 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 4 work hours per airplane to accomplish the required 
inspection, and that the average labor rate is $60 per work hour. Based 
on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $17,520, or $240 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 53473]]

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-16-11 Boeing: Amendment 39-12850. Docket 2000-NM-333-AD.

    Applicability: Model 777 series airplanes, line numbers 1 
through 263 inclusive; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent breakage of the aft axle pivot pin of the main 
landing gear (MLG), which could overload the center axle, causing 
the tires to blow out upon landing, and could disengage the aft axle 
so that it jams the gear in the wheel well, preventing proper 
extension of the MLG, accomplish the following:

Inspection

    (a) Within 18 months after the effective date of this AD: 
Perform the actions specified in paragraph (a)(1) or (a)(2) of this 
AD, as applicable, in accordance with Boeing Special Attention 
Service Bulletin 777-32-0029, dated May 18, 2000.
    (1) For airplanes which have line numbers 1 through 68 inclusive 
(designated as Group 1 airplanes in the service bulletin), and on 
which the aft axle pivot pin of the MLG has been replaced prior to 
the effective date of this AD: Inspect the serial number of the 
pivot pin.
    (i) If the serial number of the pivot pin does not have the 
prefix of EGL, no further action is required.
    (ii) If the serial number of the pivot pin does have the prefix 
of EGL, within 18 months after the effective date of this AD, 
perform the actions required by paragraph (a)(2) of this AD.
    (2) For airplanes which have line numbers 69 through 263 
inclusive (designated as Group 2 airplanes in the service bulletin): 
Remove the aft axle pivot pin, remove the lube insert from the aft 
axle pivot pin, and inspect the aft axle pivot pin for heat damage. 
The inspection must be done either by the Barkhausen Noise 
Inspection method for chromium-plated parts, or by following all of 
the procedures in Figure 2 of the service bulletin (including nital 
etching and a magnetic particle inspection), in accordance with the 
service bulletin.
    (i) If heat damage is found by the inspection required by 
paragraph (a)(2) of this AD: Prior to further flight, re-work the 
existing aft axle pivot pin, re-install the existing lube insert, 
and re-install the re-worked aft axle pivot pin or install a new or 
serviceable aft axle pivot pin in the MLG, in accordance with the 
service bulletin.
    (ii) If no heat damage is found by the inspection required by 
paragraph (a)(2) of this AD: Prior to further flight, re-install the 
existing lube insert and re-install the existing aft axle pivot pin 
or install a new or serviceable aft axle pivot pin in the MLG, in 
accordance with the service bulletin.

Spares

    (b) After the effective date of this AD, no person shall install 
an aft axle pivot pin having a serial number with the prefix ``EGL'' 
in the MLG, unless the pivot pin has been inspected as required by 
paragraph (a) of this AD.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.

Incorporation by Reference

    (e) The actions shall be done in accordance with Boeing Special 
Attention Service Bulletin 777-32-0029, dated May 18, 2000. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, PO 
Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (f) This amendment becomes effective on September 20, 2002.

    Issued in Renton, Washington, on August 7, 2002.
Vi Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20510 Filed 8-15-02; 8:45 am]
BILLING CODE 4910-13-P