Airworthiness Directives; Boeing Model 777 Airplanes, 70860-70862 [E6-20624]

Download as PDF 70860 Federal Register / Vol. 71, No. 235 / Thursday, December 7, 2006 / Rules and Regulations DEPARTMENT OF TRANSPORTATION SUPPLEMENTARY INFORMATION: Federal Aviation Administration Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://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 street address stated in the ADDRESSES section. 14 CFR Part 39 [Docket No. FAA–2006–23817; Directorate Identifier 2005–NM–176–AD; Amendment 39–14846; AD 2006–25–05] RIN 2120–AA64 Airworthiness Directives; Boeing Model 777 Airplanes sroberts on PROD1PC70 with RULES AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777 airplanes. This AD requires repetitive inspections for corrosion or missing corrosion inhibiting compound of the fuselage skin under the forward and aft wing-tobody fairings for certain airplanes, or the fuselage skin under the forward wing-to-body fairings only for other airplanes; and corrective action if necessary. The AD also provides an optional preventive modification of the fairing areas, which terminates the repetitive inspections. This AD results from several reports indicating that significant levels of corrosion were found on the external surface of the fuselage skin under the forward and aft wing-to-body fairings. We are issuing this AD to detect and correct corrosion, and prevent subsequent fatigue cracks, on the fuselage skin under the forward and aft wing-to-body fairings, which could result in rapid decompression of the airplane. DATES: This AD becomes effective January 11, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of January 11, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6443; fax (425) 917–6590. VerDate Aug<31>2005 20:43 Dec 06, 2006 Jkt 211001 Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Boeing Model 777 airplanes. That NPRM was published in the Federal Register on February 8, 2006 (71 FR 6402). That NPRM proposed to require repetitive inspections for corrosion or missing corrosion inhibiting compound (CIC) of the fuselage skin under the forward and aft wing-to-body fairings for certain airplanes, or the fuselage skin under the forward wing-to-body fairings only for other airplanes; and corrective action if necessary. That NPRM also proposed to provide an optional preventive modification of the wing-to-body fairing panels, which would terminate the repetitive inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Include Revised Service Information Continental Airlines (CAL) asks that the NPRM mandate Revision 1 of the referenced service bulletin when it becomes available, instead of the original issue. (Boeing Alert Service Bulletin 777–53A0044, dated July 28, 2005, was referenced in the NPRM as the appropriate source of service information for accomplishing the specified actions.) CAL states that it found some discrepancies in the instructions in Part 2 of the service bulletin during incorporation of the preventive modification specified in the original issue of the service bulletin. CAL adds that those discrepancies need clarification in order to meet the scope of the service bulletin and the objective of the NPRM. CAL notes that the instructions specified in Figures 11 and 15 of the original issue of the service bulletin are misleading and can cause incorrect assumptions and actions when implemented. CAL coordinated with PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Boeing to obtain clarification and enhancement of the instructions specified in Figures 11 and 15. CAL notes that the corrected instructions will be incorporated into Revision 1 of the service bulletin by Boeing. We partially agree with CAL. Boeing has issued Service Bulletin 777– 53A0044, Revision 1, dated June 22, 2006, which we have subsequently reviewed. We agree to include Revision 1 of the referenced service bulletin in the AD as the appropriate source of service information for accomplishing the specified actions. Revision 1 is essentially the same as the original issue of the service bulletin; however, Revision 1 recommends that airplanes in Groups 1 and 4 that have been previously changed per the original issue of the service bulletin be inspected at the next scheduled under-fairing zonal or surveillance inspections. This is to ensure that the fastener fillet sealing at body stations 1035 and 1434 are in compliance with Figures 11, 15, and 20, as applicable, of Revision 1. The original issue of the service bulletin identified airplanes that were divided into Groups 1 and 2. Revision 1 of the service bulletin divides the airplanes into Groups 1 through 6; however, there is no increase in the number of airplanes. We do not agree to remove reference to the original issue of the service bulletin and refer to only Revision 1, because operators who previously did the required actions in accordance with the original issue of the service bulletin would then be out of compliance as of the effective date of the new AD. We find that actions done before the effective date of this AD in accordance with the instructions in the original issue of the service bulletin will provide an acceptable level of safety until the newly required actions are done. We have changed paragraph (h) of this AD to add the following sentence: ‘‘After the effective date of this AD, only Revision 1 of the service bulletin may be used for accomplishing the preventive modification.’’ Although no more work is necessary on airplanes changed per the original issue of the service bulletin; it is recommended that airplanes in Groups 1 and 4 which have been previously changed per the original issue, be inspected at the next scheduled under-fairing zonal or surveillance inspections as specified above. Request To Change Paragraph (h) Boeing asks that the language for the optional terminating action specified in paragraph (h) of the NPRM be changed. E:\FR\FM\07DER1.SGM 07DER1 Federal Register / Vol. 71, No. 235 / Thursday, December 7, 2006 / Rules and Regulations Boeing reiterates that paragraph and states that it should be changed to read ‘‘Accomplishing the preventive modification in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777– 53A0044, dated July 28, 2005, terminates the repetitive inspections required by paragraph (f) of this AD.’’ Boeing states that, in the forward fairing area the preventive modification consists of modification to the forward body fairing panels, as well as addition of fastener head fillet sealing and revised CIC in specific areas above the wing body fairing panels. Boeing adds that, in the aft fairing area, the preventive modification consists of fastener head fillet sealing and revised CIC in specific areas above the wing body fairing panels. Boeing states that there is no change to the wing-to-body fairing panels in the aft fairing area, and the proposed wording could be interpreted as not providing a terminating action for the aft fairing area. Boeing notes that this is inconsistent with the referenced service bulletin, and changing the language would make the NPRM consistent with the service bulletin. We agree with Boeing for the reasons provided. We have changed the subject language in the Summary section. We have also changed the language in paragraph (h) of this AD to read ‘‘Accomplishing the preventive modification of the fairing areas in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0044, dated July 28, 2005; or Boeing Service Bulletin 777–53A0044, Revision 1, dated June 22, 2006; terminates the repetitive inspections required by paragraph (f) of this AD.’’ Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. These changes will neither increase the economic burden on any operator nor increase the scope of the AD. sroberts on PROD1PC70 with RULES Costs of Compliance There are about 385 airplanes of the affected design in the worldwide fleet. This AD affects about 140 airplanes of U.S. registry. The inspection takes about 8 work hours per airplane for Groups 1, 3, 4, and 5 airplanes, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the VerDate Aug<31>2005 20:43 Dec 06, 2006 Jkt 211001 inspection for U.S. operators is $520 per airplane, per inspection cycle. The inspection takes about 4 work hours per airplane for Groups 2 and 6 airplanes, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the inspection for U.S. operators is $260 per airplane, per inspection cycle. 70861 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: n PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: n 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 and placed it in the AD docket. 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): n 2006–25–05 Boeing: Amendment 39–14846. Docket No. FAA–2006–23817; Directorate Identifier 2005–NM–176–AD. Effective Date (a) This AD becomes effective January 11, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 777– 200, –300, and –300ER series airplanes; certificated in any category; as identified in Boeing Service Bulletin 777–53A0044, Revision 1, dated June 22, 2006. Unsafe Condition (d) This AD results from several reports indicating that significant levels of corrosion were found on the external surface of the fuselage skin under the forward and aft wingto-body fairings. We are issuing this AD to detect and correct corrosion, and prevent subsequent fatigue cracks, on the fuselage skin under the forward and aft wing-to-body fairings, which could result in 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. Repetitive Inspections (f) At the latest of the compliance times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD, as applicable: Perform a detailed inspection of the fuselage skin under the wing-to-body fairings for corrosion or missing corrosion inhibiting compound (CIC) by doing all the applicable actions specified in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777– 53A0044, dated July 28, 2005; or Boeing Service Bulletin 777–53A0044, Revision 1, dated June 22, 2006. Repeat the inspection thereafter at intervals not to exceed 1,500 days until the requirements of paragraph (h) of this AD are accomplished. (1) Before the accumulation of 1,500 days since the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. E:\FR\FM\07DER1.SGM 07DER1 70862 Federal Register / Vol. 71, No. 235 / Thursday, December 7, 2006 / Rules and Regulations (2) Within 1,500 days after accomplishing the latest zonal or surveillance inspection before the effective date of this AD that is equivalent to the detailed inspection specified in paragraph (f) of this AD. (3) Within 750 days after the effective date of this AD. Corrective Action (g) If any corrosion or missing CIC is found during any inspection required by paragraph (f) of this AD: Before further flight, do a detailed inspection to determine the full extent of the corrosion; repair before further flight by doing all the applicable actions specified in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0044, dated July 28, 2005; or Boeing Service Bulletin 777–53A0044, Revision 1, dated June 22, 2006. Where the service bulletin specifies to contact Boeing for repair instructions: Repair before further flight, according to a method approved in accordance with the procedures specified in paragraph (i) of this AD. Optional Terminating Action (h) Accomplishing the preventive modification of the fairing areas in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0044, dated July 28, 2005; or Boeing Service Bulletin 777– 53A0044, Revision 1, dated June 22, 2006; terminates the repetitive inspections required by paragraph (f) of this AD. After the effective date of this AD, only Revision 1 of the service bulletin may be used for accomplishing the preventive modification. sroberts on PROD1PC70 with RULES Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (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) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) 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 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. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 777–53A0044, dated July 28, 2005; or Boeing Service Bulletin 777–53A0044, Revision 1, dated June 22, 2006; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. VerDate Aug<31>2005 20:43 Dec 06, 2006 Jkt 211001 Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at 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 https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20624 Filed 12–6–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25634; Directorate Identifier 2006–NM–143–AD; Amendment 39–14844; AD 2006–25–03] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of pitch trim system 2 to deflect the trimmable horizontal stabilizer at maximum rate, which could result in loss of high-speed trim and consequent reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 11, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 11, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 SW., Nassif Building, Room PL–401, Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3371; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to allow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 18, 2006 (71 FR 47752). That NPRM proposed to require a periodic test to ensure the availability of the pitch trim system 2 and its possibility to deflect the trimmable horizontal stabilizer (THS) at high speed of trim. The MCAI states that the refined study of an in-service event has evidenced the need to perform a periodic test of pitch trim system 2. In the conditions of overriding the automatic pitch torque limiter, the clutch of the pitch trim servo-motor 1 is opened so that electric pitch trim system 1 will disconnect. The question is pending about the availability of the system 2 and its capability to take over the pitch trim function, particularly during a go-around. Failure of pitch trim system 2 to deflect the THS at maximum rate could result in loss of high-speed trim and consequent reduced controllability of the airplane. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received from one commenter. E:\FR\FM\07DER1.SGM 07DER1

Agencies

[Federal Register Volume 71, Number 235 (Thursday, December 7, 2006)]
[Rules and Regulations]
[Pages 70860-70862]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20624]



[[Page 70860]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23817; Directorate Identifier 2005-NM-176-AD; 
Amendment 39-14846; AD 2006-25-05]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777 Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing Model 777 airplanes. This AD requires repetitive 
inspections for corrosion or missing corrosion inhibiting compound of 
the fuselage skin under the forward and aft wing-to-body fairings for 
certain airplanes, or the fuselage skin under the forward wing-to-body 
fairings only for other airplanes; and corrective action if necessary. 
The AD also provides an optional preventive modification of the fairing 
areas, which terminates the repetitive inspections. This AD results 
from several reports indicating that significant levels of corrosion 
were found on the external surface of the fuselage skin under the 
forward and aft wing-to-body fairings. We are issuing this AD to detect 
and correct corrosion, and prevent subsequent fatigue cracks, on the 
fuselage skin under the forward and aft wing-to-body fairings, which 
could result in rapid decompression of the airplane.

DATES: This AD becomes effective January 11, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of January 11, 
2007.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
AD.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6443; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Boeing Model 
777 airplanes. That NPRM was published in the Federal Register on 
February 8, 2006 (71 FR 6402). That NPRM proposed to require repetitive 
inspections for corrosion or missing corrosion inhibiting compound 
(CIC) of the fuselage skin under the forward and aft wing-to-body 
fairings for certain airplanes, or the fuselage skin under the forward 
wing-to-body fairings only for other airplanes; and corrective action 
if necessary. That NPRM also proposed to provide an optional preventive 
modification of the wing-to-body fairing panels, which would terminate 
the repetitive inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Include Revised Service Information

    Continental Airlines (CAL) asks that the NPRM mandate Revision 1 of 
the referenced service bulletin when it becomes available, instead of 
the original issue. (Boeing Alert Service Bulletin 777-53A0044, dated 
July 28, 2005, was referenced in the NPRM as the appropriate source of 
service information for accomplishing the specified actions.) CAL 
states that it found some discrepancies in the instructions in Part 2 
of the service bulletin during incorporation of the preventive 
modification specified in the original issue of the service bulletin. 
CAL adds that those discrepancies need clarification in order to meet 
the scope of the service bulletin and the objective of the NPRM. CAL 
notes that the instructions specified in Figures 11 and 15 of the 
original issue of the service bulletin are misleading and can cause 
incorrect assumptions and actions when implemented. CAL coordinated 
with Boeing to obtain clarification and enhancement of the instructions 
specified in Figures 11 and 15. CAL notes that the corrected 
instructions will be incorporated into Revision 1 of the service 
bulletin by Boeing.
    We partially agree with CAL. Boeing has issued Service Bulletin 
777-53A0044, Revision 1, dated June 22, 2006, which we have 
subsequently reviewed.
    We agree to include Revision 1 of the referenced service bulletin 
in the AD as the appropriate source of service information for 
accomplishing the specified actions. Revision 1 is essentially the same 
as the original issue of the service bulletin; however, Revision 1 
recommends that airplanes in Groups 1 and 4 that have been previously 
changed per the original issue of the service bulletin be inspected at 
the next scheduled under-fairing zonal or surveillance inspections. 
This is to ensure that the fastener fillet sealing at body stations 
1035 and 1434 are in compliance with Figures 11, 15, and 20, as 
applicable, of Revision 1. The original issue of the service bulletin 
identified airplanes that were divided into Groups 1 and 2. Revision 1 
of the service bulletin divides the airplanes into Groups 1 through 6; 
however, there is no increase in the number of airplanes.
    We do not agree to remove reference to the original issue of the 
service bulletin and refer to only Revision 1, because operators who 
previously did the required actions in accordance with the original 
issue of the service bulletin would then be out of compliance as of the 
effective date of the new AD. We find that actions done before the 
effective date of this AD in accordance with the instructions in the 
original issue of the service bulletin will provide an acceptable level 
of safety until the newly required actions are done. We have changed 
paragraph (h) of this AD to add the following sentence: ``After the 
effective date of this AD, only Revision 1 of the service bulletin may 
be used for accomplishing the preventive modification.'' Although no 
more work is necessary on airplanes changed per the original issue of 
the service bulletin; it is recommended that airplanes in Groups 1 and 
4 which have been previously changed per the original issue, be 
inspected at the next scheduled under-fairing zonal or surveillance 
inspections as specified above.

Request To Change Paragraph (h)

    Boeing asks that the language for the optional terminating action 
specified in paragraph (h) of the NPRM be changed.

[[Page 70861]]

Boeing reiterates that paragraph and states that it should be changed 
to read ``Accomplishing the preventive modification in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-53A0044, dated July 28, 2005, terminates the repetitive 
inspections required by paragraph (f) of this AD.'' Boeing states that, 
in the forward fairing area the preventive modification consists of 
modification to the forward body fairing panels, as well as addition of 
fastener head fillet sealing and revised CIC in specific areas above 
the wing body fairing panels. Boeing adds that, in the aft fairing 
area, the preventive modification consists of fastener head fillet 
sealing and revised CIC in specific areas above the wing body fairing 
panels. Boeing states that there is no change to the wing-to-body 
fairing panels in the aft fairing area, and the proposed wording could 
be interpreted as not providing a terminating action for the aft 
fairing area. Boeing notes that this is inconsistent with the 
referenced service bulletin, and changing the language would make the 
NPRM consistent with the service bulletin.
    We agree with Boeing for the reasons provided. We have changed the 
subject language in the Summary section. We have also changed the 
language in paragraph (h) of this AD to read ``Accomplishing the 
preventive modification of the fairing areas in accordance with Part 2 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
777-53A0044, dated July 28, 2005; or Boeing Service Bulletin 777-
53A0044, Revision 1, dated June 22, 2006; terminates the repetitive 
inspections required by paragraph (f) of this AD.''

Conclusion

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

Costs of Compliance

    There are about 385 airplanes of the affected design in the 
worldwide fleet. This AD affects about 140 airplanes of U.S. registry.
    The inspection takes about 8 work hours per airplane for Groups 1, 
3, 4, and 5 airplanes, at an average labor rate of $65 per work hour. 
Based on these figures, the estimated cost of the inspection for U.S. 
operators is $520 per airplane, per inspection cycle.
    The inspection takes about 4 work hours per airplane for Groups 2 
and 6 airplanes, at an average labor rate of $65 per work hour. Based 
on these figures, the estimated cost of the inspection for U.S. 
operators is $260 per airplane, per inspection 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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-25-05 Boeing: Amendment 39-14846. Docket No. FAA-2006-23817; 
Directorate Identifier 2005-NM-176-AD.

Effective Date

    (a) This AD becomes effective January 11, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 777-200, -300, and -300ER 
series airplanes; certificated in any category; as identified in 
Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 
2006.

Unsafe Condition

    (d) This AD results from several reports indicating that 
significant levels of corrosion were found on the external surface 
of the fuselage skin under the forward and aft wing-to-body 
fairings. We are issuing this AD to detect and correct corrosion, 
and prevent subsequent fatigue cracks, on the fuselage skin under 
the forward and aft wing-to-body fairings, which could result in 
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.

Repetitive Inspections

    (f) At the latest of the compliance times specified in 
paragraphs (f)(1), (f)(2), and (f)(3) of this AD, as applicable: 
Perform a detailed inspection of the fuselage skin under the wing-
to-body fairings for corrosion or missing corrosion inhibiting 
compound (CIC) by doing all the applicable actions specified in Part 
1 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 777-53A0044, dated July 28, 2005; or Boeing Service 
Bulletin 777-53A0044, Revision 1, dated June 22, 2006. Repeat the 
inspection thereafter at intervals not to exceed 1,500 days until 
the requirements of paragraph (h) of this AD are accomplished.
    (1) Before the accumulation of 1,500 days since the date of 
issuance of the original standard airworthiness certificate or the 
date of issuance of the original export certificate of 
airworthiness.

[[Page 70862]]

    (2) Within 1,500 days after accomplishing the latest zonal or 
surveillance inspection before the effective date of this AD that is 
equivalent to the detailed inspection specified in paragraph (f) of 
this AD.
    (3) Within 750 days after the effective date of this AD.

Corrective Action

    (g) If any corrosion or missing CIC is found during any 
inspection required by paragraph (f) of this AD: Before further 
flight, do a detailed inspection to determine the full extent of the 
corrosion; repair before further flight by doing all the applicable 
actions specified in Part 1 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 777-53A0044, dated July 28, 2005; or 
Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 
2006. Where the service bulletin specifies to contact Boeing for 
repair instructions: Repair before further flight, according to a 
method approved in accordance with the procedures specified in 
paragraph (i) of this AD.

Optional Terminating Action

    (h) Accomplishing the preventive modification of the fairing 
areas in accordance with Part 2 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 777-53A0044, dated July 28, 2005; 
or Boeing Service Bulletin 777-53A0044, Revision 1, dated June 22, 
2006; terminates the repetitive inspections required by paragraph 
(f) of this AD. After the effective date of this AD, only Revision 1 
of the service bulletin may be used for accomplishing the preventive 
modification.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (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) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) 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 
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.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 777-53A0044, 
dated July 28, 2005; or Boeing Service Bulletin 777-53A0044, 
Revision 1, dated June 22, 2006; as applicable; to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference of these documents in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial 
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy 
of this service information. You may review copies at the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street, SW., Room PL-401, Nassif Building, Washington, DC; on the 
Internet at https://dms.dot.gov; or at 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 https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

    Issued in Renton, Washington, on November 20, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-20624 Filed 12-6-06; 8:45 am]
BILLING CODE 4910-13-P

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