Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes

[Federal Register Volume 67, Number 105 (Friday, May 31, 2002)]
[Rules and Regulations]
[Pages 37975-37976]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-13607]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-38-AD; Amendment 39-12714; AD 2002-08-06]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200 and -300 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to certain Boeing Model 777-
200 and -300 series airplanes. That AD currently requires a one-time 
torque check (inspection) of the bolts that attach the pivot fittings 
to the horizontal stabilizer through the upper and lower titanium 
straps, to determine if the bolts are adequately torqued, and follow-on 
actions. This document corrects the requirements of the existing AD by 
adding an option to allow operators a 30-day grace period for 
submission of the report required by paragraph (d) of the AD. This 
correction is prompted by communication received from the manufacturer 
that the current requirements of the AD could put operators out of 
compliance.

DATES: Effective May 3, 2002.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of May 3, 2002 (67 FR 19104, April 18, 2002).

FOR FURTHER INFORMATION CONTACT: John Craycraft, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2782; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: On April 11, 2002, the Federal Aviation 
Administration (FAA) issued AD 2002-08-06, amendment 39-12714 (67 FR 
19104, April 18, 2002), applicable to certain Boeing Model 777-200 and 
-300 series airplanes. That AD requires a one-time torque check 
(inspection) of the bolts that attach the pivot fittings to the 
horizontal stabilizer through the upper and lower titanium straps, to 
determine if the bolts are adequately torqued, and follow-on actions. 
The actions required by that AD are intended to prevent failure of the 
pivot fittings, which could result in loss of control of the horizontal 
stabilizer and consequent loss of control of the airplane.

Need for the Correction

    Information obtained recently from the manufacturer indicates that 
the compliance time for the reporting requirement in paragraph (d) of 
AD 2002-08-06 does not allow operators who have already done the 
inspection required by paragraph (a) of the AD enough time to submit 
the required information.
    The FAA has determined that a correction to AD 2002-08-06 is 
necessary. The correction will add an option to allow operators a 30-
day grace period for submission of the reporting requirements specified 
in paragraph (d) of the AD. The correction will add sub-paragraphs 
(d)(1) and (d)(2) to the AD to include that option.

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains May 3, 2002.
    Since this action only corrects a current requirement, it has no 
adverse economic impact and imposes no additional burden on any person. 
Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

[[Page 37976]]

List of Subjects in 14 CFR Part 39

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

Adoption of the Correction

    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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2002-08-06  Boeing: Amendment 39-12714. Docket 2002-NM-38-AD.

    Applicability: Model 777-200 and -300 series airplanes as listed 
in Boeing Alert Service Bulletin 777-55A0013, Revision 1, dated 
January 31, 2002; 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 (e) 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 failure of the pivot fittings of the horizontal 
stabilizer, which could result in loss of control of the horizontal 
stabilizer and consequent loss of control of the airplane, 
accomplish the following:

Torque Check (Inspection)

    (a) Within 90 days after the effective date of this AD, do the 
following inspections of the aft bolts of the pivot fittings 
attached to the horizontal stabilizer, per the Accomplishment 
Instructions of Boeing Alert Service Bulletin 777-55A0013, Revision 
1, dated January 31, 2002:
    (1) Do a torque check (inspection) to determine if the bolts are 
adequately torqued per the service bulletin.
    (2) Do a detailed inspection of the bolt thread protrusion 
through the nut. Replace any bolt that has less than the chamfer of 
the bolt or more than three threads protruding through the nut per 
Steps 6.d. and 6.e. or Steps 7.d. and 7.e. of the Work Instructions 
of the service bulletin for Group 1 or Group 2 airplanes, as 
applicable.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''


    Note 3: For Group 1 airplanes and Group 2 airplanes with WBnnn 
variable numbers (where nnn is any three digits), inspections and 
follow-on actions done before the effective date of this AD per 
Boeing Service Bulletin 777-55A0013, dated December 19, 2001, are 
considered acceptable for compliance with the corresponding actions 
specified in paragraph (a)(1) of this AD.

 1Follow-On Actions

    (3) Do Steps 8. and 9. of the Work Instructions in Part B of the 
service bulletin, if the torque value of all attachment bolts is 
found to be within the specified limits, then no further action is 
required by this AD.
    (b) During the inspection required by paragraph (a)(1) of this 
AD, if the torque value of any attachment bolt is found to be less 
than or equal to the value specified in Step 4. of the Work 
Instructions of Boeing Alert Service Bulletin 777-55A0013, Revision 
1, dated January 31, 2002: Before further flight, do all actions 
(includes removing the nut and measuring run-on torque; replacing 
any nut that does not meet the run-on torque requirements; doing a 
visual inspection for indications of galling, fretting, and wear; 
replacing the bolt if any discrepancies are found; and doing an 
open-hole high frequency eddy current (HFEC) inspection for cracks); 
as specified in and per Steps 5., 6., and 7., as applicable, of the 
Work Instructions of Boeing Alert Service Bulletin 777-55A0013, 
Revision 1, dated January 31, 2002, for Group 1 or Group 2 
airplanes, as applicable.
    (c) If any cracking is found during the HFEC inspection and the 
service bulletin specifies contacting Boeing for repair 
instructions: Before further flight, repair per 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.

Reporting Requirement

    (d) After doing the inspections required by paragraph (a) of 
this AD: Submit a report of the bolt torque values and run-on torque 
values of the nut, and/or any damaged areas found, to the FAA 
Certification Management Office--Boeing, ANM-108B, 1601 Lind Avenue, 
SW., Renton, Washington 98055-4056, at the applicable time specified 
in paragraph (d)(1) or (d)(2) of this AD. Information collection 
requirements contained in this AD have been approved by the Office 
of Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the inspection is done after the 
effective date of this AD: Submit the report within 10 days after 
doing the inspection.
    (2) For airplanes on which the inspection was done before the 
effective date of this AD: Submit the report within 30 days after 
the effective date of this AD.

Alternative Methods of Compliance

    (e) 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 ACO. 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 4: 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

    (f) Special flight permits may be issued in accordance with 
sections 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

    (g) Except as provided by paragraph (c) of this AD, the actions 
shall be done in accordance with Boeing Alert Service Bulletin 777-
55A0013, Revision 1, dated January 31, 2002. This incorporation by 
reference was approved previously by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of 
May 3, 2002 (67 FR 19104, April 18, 2002). Copies may be obtained 
from Boeing Commercial Airplane Group, P.O. 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

    (h) The effective date of this amendment remains May 3, 2002.

    Issued in Renton, Washington, on May 23, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-13607 Filed 5-30-02; 8:45 am]
BILLING CODE 4910-13-P

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