Airworthiness Directives; Boeing Model 767-300F Series Airplanes, 69583-69585 [E7-23685]

Download as PDF Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations (2) The applicant may demonstrate by a system test and analysis that the electrical and electronic systems that perform critical functions can withstand a minimum threat of 100 volts per meter, electrical field strength, from 10 kHz to 18 GHz. When using this test to show compliance with the HIRF requirements, no credit is given for signal attenuation due to installation. A preliminary hazard analysis must be performed by the applicant, for approval by the FAA, to identify either electrical or electronic systems that perform critical functions. The term ‘‘critical’’ means those functions, whose failure would contribute to, or cause, a failure condition that would prevent the continued safe flight and landing of the airplane. The systems identified by the hazard analysis that perform critical functions are candidates for the application of HIRF requirements. A system may perform both critical and non-critical functions. Primary electronic flight display systems, and their associated components, perform critical functions such as attitude, altitude, and airspeed indication. The HIRF requirements apply only to critical functions. Compliance with HIRF requirements may be demonstrated by tests, analysis, models, similarity with existing systems, or any combination of these. Service experience alone is not acceptable since normal flight operations may not include an exposure to the HIRF environment. Reliance on a system with similar design features for redundancy as a means of protection against the effects of external HIRF is generally insufficient since all elements of a redundant system are likely to be exposed to the fields concurrently. Applicability As discussed above, these special conditions are applicable to one modification to the aircraft models listed under the heading ‘‘Type Certification Basis.’’ Should ASPEN Avionics Inc., apply at a later date to extend this modification to include additional airplane models, the special conditions would apply to that model as well under the provisions of § 21.101. mstockstill on PROD1PC66 with RULES Conclusion This action affects only certain novel or unusual design features on one modification to the aircraft models listed under the heading ‘‘Type Certification Basis.’’ It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplane. VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. For this reason, and because a delay would significantly affect the certification of the airplane, which is imminent, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.101; and 14 CFR 11.38 and 11.19. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the EFD 1000 EFIS manufactured by ASPEN Avionics Inc. 1. Protection of Electrical and Electronic Systems from High Intensity Radiated Fields (HIRF). Each system that performs critical functions must be designed and installed to ensure that the operations, and operational capabilities of these systems to perform critical functions, are not adversely affected when the airplane is exposed to high intensity radiated electromagnetic fields external to the airplane. 2. For the purpose of these special conditions, the following definition applies: Critical Functions: Functions whose failure would contribute to, or cause, a failure condition that would prevent the continued safe flight and landing of the airplane. Issued in Kansas City, Missouri on November 30, 2007. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23835 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 69583 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28943; Directorate Identifier 2007–NM–011–AD; Amendment 39–15295; AD 2007–25–13] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–300F Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767–300F series airplanes. This AD requires replacing the rotomolded duct(s) of the mix manifold system with new duct(s). This AD results from a report of failures of the duct joint seal of the mix manifold system. We are issuing this AD to prevent air conditioning leakage into the mix manifold bay. Such leakage could decrease the air flow to the flight compartment and main cabin or could allow smoke into the flight compartment in the event of a fire in the main cabin or forward cargo compartment. This AD becomes effective January 14, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 14, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Jeffrey S. Palmer, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, E:\FR\FM\10DER1.SGM 10DER1 69584 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6481; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: 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 767–300F series airplanes. That NPRM was published in the Federal Register on August 16, 2007 (72 FR 45980). That NPRM proposed to require replacing the rotomolded duct(s) of the mix manifold system with new duct(s). Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Boeing supports the NPRM. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 40 airplanes of the affected design in the worldwide fleet. This AD affects about 32 airplanes of U.S. registry. The required actions will take about 2 or 8 work hours per airplane, at an average labor rate of $80 per work hour. Required parts will cost about $4,123 or $42,825 per airplane. Based on these figures, the estimated cost of the AD for U.S. operators is $4,283 or $43,465 per airplane. (The estimated work hours and costs depend on the airplane configuration). 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 Accordingly, under the authority delegated to me by the Administrator, I the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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): I 2007–25–13 Boeing: Amendment 39–15295. Docket No. FAA–2007–28943; Directorate Identifier 2007–NM–011–AD. Effective Date (a) This AD becomes effective January 14, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 767– 300F series airplanes, certificated in any category; as identified in Boeing Special Attention Service Bulletin 767–21–0192, dated March 23, 2006. Unsafe Condition (d) This AD results from a report of failures of the duct joint seal of the mix manifold system. We are issuing this AD to prevent air conditioning leakage into the mix manifold bay. Such leakage could decrease the air flow to the flight compartment and main cabin or could allow smoke into the flight compartment in the event of a fire in the main cabin or forward cargo compartment. 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. Replacement (f) Within 36 months after the effective date of this AD, do the applicable action specified in Table 1 of this AD in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–21–0192, dated March 23, 2006. TABLE 1.—REPLACEMENT For airplanes identified in the service bulletin as— Do the following action— (1) Group 1 airplanes ..... Replace the rotomolded duct between the transition duct of the right cooling pack and the mix manifold with a new duct made of aluminum. Replace the rotomolded ducts of the mix manifold system with new ducts made from Kevlar and aluminum. mstockstill on PROD1PC66 with RULES (2) Group 2 airplanes ..... Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District E:\FR\FM\10DER1.SGM 10DER1 Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations Office (FSDO), or lacking a PI, your local FSDO. 69585 levels less than 9g during an emergency landing, which could cause injury to passengers and/or crew and could impede subsequent rapid evacuation. DATES: This AD is effective December 26, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 26, 2007. We must receive comments on this AD by February 8, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. requirement. As a result, the overhead lateral shear beam at that door reacts to loads from the weight of the center stowage bins of zone E and to additional loads due to galleys, life raft boxes, closets, and partitions (depending on airplane configuration). This condition, if not corrected, could result in detachment of the center stowage bins of zone E at forward load levels less than 9g during an emergency landing, which could cause injury to passengers and/or crew and could impede subsequent rapid evacuation. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2007–0301; Directorate Identifier 2007–NM–069–AD; Amendment 39–15300; AD 2007–25–18] You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Rene Buendia, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6448; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: No airplanes affected by this AD are on the U.S. Register. We are issuing this AD because the unsafe condition described previously is likely to exist or develop on other products of the(se) same type design(s) that could be registered in the United States in the future. This AD requires modifying the stowage bin ladder of zone E, installing new intercostals, removing existing tie rods, and installing new tie rods. For certain other airplanes, this AD requires modifying the lateral shear beam. Since no airplanes are affected by this AD, notice and opportunity for public comment before issuing this AD are unnecessary. Material Incorporated by Reference (h) You must use Boeing Special Attention Service Bulletin 767–21–0192, dated March 23, 2006, 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 this document 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 FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at 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 23, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23685 Filed 12–7–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400 and 747–400D Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. mstockstill on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747–400 and 747–400D series airplanes. For certain airplanes, this AD requires modifying the stowage bin ladder of zone E, installing new intercostals, removing existing tie rods, and installing new tie rods. For certain other airplanes, this AD requires modifying the lateral shear beam. This AD results from a report indicating that the overhead lateral shear beam aft of main entry door number 5 reacts to certain loads from the weight of the center stowage bins of zone E and additional loads. We are issuing this AD to prevent detachment of the center stowage bins of zone E at forward load VerDate Aug<31>2005 16:20 Dec 07, 2007 Jkt 214001 Discussion We have received a report indicating that a review, at Boeing, of the airplane interior loads on certain Boeing Model 747–400 and 747–400D series airplanes without a door 5 crew rest, showed that the overhead lateral shear beam aft of main entry door number 5 does not meet the 9g forward loading PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 747–53– 2498, dated December 19, 2006. For certain airplanes, the service bulletin describes procedures for modifying the stowage bin ladder of zone E by installing new tie rod fittings, installing new right and left intercostals, and removing existing tie rods. For certain other airplanes, the service bulletin describes procedures for modifying the lateral shear beam by installing additional stiffeners. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of This AD Costs of Compliance None of the airplanes affected by this action are on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future. The following table provides the estimated costs for U.S. operators to comply with this AD for any affected E:\FR\FM\10DER1.SGM 10DER1

Agencies

[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Rules and Regulations]
[Pages 69583-69585]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23685]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28943; Directorate Identifier 2007-NM-011-AD;
Amendment 39-15295; AD 2007-25-13]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 767-300F Series 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 767-300F series airplanes. This AD requires
replacing the rotomolded duct(s) of the mix manifold system with new
duct(s). This AD results from a report of failures of the duct joint
seal of the mix manifold system. We are issuing this AD to prevent air
conditioning leakage into the mix manifold bay. Such leakage could
decrease the air flow to the flight compartment and main cabin or could
allow smoke into the flight compartment in the event of a fire in the
main cabin or forward cargo compartment.

DATES: This AD becomes effective January 14, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of January 14,
2008.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Jeffrey S. Palmer, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office,

[[Page 69584]]

1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6481; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

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
767-300F series airplanes. That NPRM was published in the Federal
Register on August 16, 2007 (72 FR 45980). That NPRM proposed to
require replacing the rotomolded duct(s) of the mix manifold system
with new duct(s).

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comment received. Boeing
supports the NPRM.

Conclusion

We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD as proposed.

Costs of Compliance

There are about 40 airplanes of the affected design in the
worldwide fleet. This AD affects about 32 airplanes of U.S. registry.
The required actions will take about 2 or 8 work hours per airplane, at
an average labor rate of $80 per work hour. Required parts will cost
about $4,123 or $42,825 per airplane. Based on these figures, the
estimated cost of the AD for U.S. operators is $4,283 or $43,465 per
airplane. (The estimated work hours and costs depend on the airplane
configuration).

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):

2007-25-13 Boeing: Amendment 39-15295. Docket No. FAA-2007-28943;
Directorate Identifier 2007-NM-011-AD.

Effective Date

(a) This AD becomes effective January 14, 2008.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 767-300F series airplanes,
certificated in any category; as identified in Boeing Special
Attention Service Bulletin 767-21-0192, dated March 23, 2006.

Unsafe Condition

(d) This AD results from a report of failures of the duct joint
seal of the mix manifold system. We are issuing this AD to prevent
air conditioning leakage into the mix manifold bay. Such leakage
could decrease the air flow to the flight compartment and main cabin
or could allow smoke into the flight compartment in the event of a
fire in the main cabin or forward cargo compartment.

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.

Replacement

(f) Within 36 months after the effective date of this AD, do the
applicable action specified in Table 1 of this AD in accordance with
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 767-21-0192, dated March 23, 2006.

Table 1.--Replacement
------------------------------------------------------------------------
For airplanes identified in
the service bulletin as-- Do the following action--
------------------------------------------------------------------------
(1) Group 1 airplanes......... Replace the rotomolded duct between the
transition duct of the right cooling
pack and the mix manifold with a new
duct made of aluminum.
(2) Group 2 airplanes......... Replace the rotomolded ducts of the mix
manifold system with new ducts made
from Kevlar[reg] and aluminum.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

(g)(1) The Manager, Seattle Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District

[[Page 69585]]

Office (FSDO), or lacking a PI, your local FSDO.

Material Incorporated by Reference

(h) You must use Boeing Special Attention Service Bulletin 767-
21-0192, dated March 23, 2006, 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
this document 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 FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at 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 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-23685 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P

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