Airworthiness Directives; Boeing Model 747-200B, 747-300, 747-400, 747-400D, and 747-400F Series Airplanes Equipped with General Electric CF6-80C2 Engines, 73587-73589 [E7-24520]

Download as PDF Federal Register / Vol. 72, No. 248 / Friday, December 28, 2007 / Rules and Regulations pwalker on PROD1PC71 with RULES to cite a specific size that will apply in all installations; however, as a general rule, components with exposed-surface areas of one square foot or less may be considered small enough that they do not have to meet the new standards. Components with exposed-surface areas greater than two square feet may be considered large enough that they do have to meet the new standards. Those with exposed-surface areas greater than one square foot, but less than two square feet, must be considered in conjunction with the areas of the cabin in which they are installed before a determination could be made.’’ In the late 1990s, the FAA issued Policy Memorandum 97–112–39, Guidance for Flammability Testing of Seat/Console Installations, October 17, 1997 (https://rgl.faa.gov). That memo was issued when it became clear that seat designs were evolving to include large, non-metallic panels with surface areas that would impact survivability during a cabin fire event, comparable to partitions or galleys. The memo noted that large surface area panels must comply with heat release and smoke emission requirements, even if they were attached to a seat. If the FAA had not issued such policy, seat designs could have been viewed as a loophole to the airworthiness standards that would result in an unacceptable decrease in survivability during a cabin fire event. In October of 2004, an issue was raised regarding the appropriate flammability standards for passenger seats that incorporated non-traditional, large, non-metallic panels in lieu of the traditional metal covered by fabric. The Seattle Aircraft Certification Office and Transport Standards Staff reviewed this design and determined that it represented the kind and quantity of material that should be required to pass the heat release and smoke emissions requirements. We have determined that special conditions would be promulgated to apply the standards defined in § 25.853(d) to seats with large, non-metallic panels in their design. Discussion of Comments Notice of proposed special conditions No. 25–07–17-SC, pertaining to Boeing Model 757 series airplanes, was published in the Federal Register on November 27, 2007. No comments were received and the special conditions are adopted as proposed. Applicability As discussed above, these special conditions are applicable to Boeing Model 757 series airplanes. It is not our VerDate Aug<31>2005 23:53 Dec 27, 2007 Jkt 214001 intent, however, to require seats with large, non-metallic panels to meet § 25.853, Appendix F, parts IV and V, if they are installed in cabins of airplanes that otherwise are not required to meet these standards. Because the heat release and smoke testing requirements of § 25.853 per Appendix F, parts IV and V, are not part of the type certification basis of the Model 757, these special conditions are only applicable if the Model 757 series airplanes are in 14 CFR part 121 operations. Section 121.312 requires compliance with the heat release and smoke testing requirements of § 25.853, for certain airplanes, irrespective of the type certification bases of those airplanes. For Model 757 series airplanes, these are the airplanes that would be affected by these special conditions. Should TIMCO apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. A2NM to incorporate the same novel or unusual design feature, the special conditions would apply to that model as well. Effective Upon Issuance Under standard practice, the effective date of final special conditions would be 30 days after the date of publication in the Federal Register; however, as the delivery date for the Boeing Model 757 series airplane modified by TIMCO is imminent, the FAA finds that good cause exists to make these special conditions effective upon issuance. Conclusion This action affects only certain novel or unusual design features on one model series of airplanes. It is not a rule of general applicability and it affects only the applicant who applied to the FAA for approval of these features on the airplane. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. 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 Boeing Model 757 series airplanes modified by TIMCO. 1. Except as provided in paragraph 3 of these special conditions, compliance with Title 14 CFR part 25, Appendix F, parts IV and V, heat release and smoke emission, is required for seats that PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 73587 incorporate non-traditional, large, nonmetallic panels that may either be a single component or multiple components in a concentrated area in their design. 2. The applicant may designate up to and including 1.5 square feet of nontraditional, non-metallic panel material per seat place that does not have to comply with special condition Number 1, above. A triple seat assembly may have a total of 4.5 square feet excluded on any portion of the assembly (e.g., outboard seat place 1 square foot, middle 1 square foot, and inboard 2.5 square feet). 3. Seats do not have to meet the test requirements of Title 14 CFR part 25, Appendix F, parts IV and V, when installed in compartments that are not otherwise required to meet these requirements. Examples include: a. Airplanes with passenger capacities of 19 or less, b. Airplanes that do not have § 25.853, Amendment 25–61 or later, in their certification basis and do not need to comply with the requirements of 14 CFR 121.312, and c. Airplanes exempted from § 25.853, Amendment 25–61 or later. Issued in Renton, Washington, on December 18, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–25077 Filed 12–27–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28352; Directorate Identifier 2007–NM–037–AD; Amendment 39–15309; AD 2007–26–07] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–200B, 747–300, 747–400, 747–400D, and 747–400F Series Airplanes Equipped with General Electric CF6–80C2 Engines 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 747–200B, 747–300, 747– 400, 747–400D, and 747–400F series airplanes. This AD requires repetitive inspections of the left- and right-hand flipper door assemblies of the engine E:\FR\FM\28DER1.SGM 28DER1 73588 Federal Register / Vol. 72, No. 248 / Friday, December 28, 2007 / Rules and Regulations core cowls for migrated pins and damaged flipper doors, and corrective actions if necessary. Modification of the hinge assemblies terminates the repetitive inspections. This AD results from two reports of missing flipper doors for the engine core cowls. We are issuing this AD to detect and correct migrated hinge pins and damaged flipper doors, which could allow the flipper door to fall off, resulting in the potential for an engine fire to propagate into the flammable leakage zone of the strut and for the amount of fire extinguishing agent reaching the fire to be diluted, and subsequent uncontained fire in the engine strut. DATES: This AD becomes effective February 1, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 1, 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: Sulmo Mariano, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6501; 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 747– 200B, 747–300, 747–400, 747–400D, and 747–400F series airplanes. That NPRM was published in the Federal Register on June 5, 2007 (72 FR 31001). That NPRM proposed to require repetitive inspections of the left- and right-hand flipper door assemblies of the engine core cowls for migrated pins and damaged flipper doors, and corrective actions if necessary. That NPRM specified that the modification of the hinge assemblies 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 Clarify the Requirements Specified in Paragraph (f) of the NPRM Boeing requests that we revise paragraph (f) of the NPRM to clarify that the modification specified in Boeing Special Attention Service Bulletin 747– 71–2310, dated October 13, 2005, is necessary only if hinge pins have migrated or flipper doors are damaged or missing. Boeing states that the instruction to do all applicable corrective actions could be interpreted to mean that the proposed modification is required, regardless of the inspection findings. We agree that modification is necessary only when hinge pins have migrated or the flipper doors are damaged or missing. Both Boeing Special Attention Service Bulletin 747– 71–2310, and Rohr Service Bulletin TBC/80C2–NAC–71–035, dated October 10, 2005, clearly state that modification is necessary only when hinge pins have migrated or the flipper doors are damaged or missing. We have made no change to the AD in this regard. Request to Clarify the Requirements Specified in Paragraph (g) of the NPRM Boeing requests that we revise paragraph (g) of the NPRM to clarify that accomplishing Rohr Service Bulletin TBC/80C2–NAC–71–035, as instructed in Boeing Special Attention Service Bulletin 747–71–2310, does not necessarily result in modification of the core cowl. Boeing points out that, if the hinge pin is properly installed, modification in accordance with Rohr Service Bulletin TBC/80C2–NAC–71– 035 is not necessary. We agree with Boeing’s comment. The actions specified in Rohr Service Bulletin TBC/80C2-NAC–71–035 do not require modification if the hinge pin has not migrated and is properly peened. We have changed paragraph (g) of this AD to say that accomplishment of the Rohr service bulletin terminates the repetitive inspection requirements (for non-discrepant hinge pins) of paragraph (f) of this AD. Conclusion We reviewed the relevant data, considered the comments received from the single commenter, and determined that air safety and the public interest require adopting the AD with the change described previously. We also determined that this change will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance There are about 297 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Inspection of flipper door assemblies, per inspection cycle. Modification of hinge assemblies, if accomplished. pwalker on PROD1PC71 with RULES Jkt 214001 $80 $0 1 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 23:53 Dec 27, 2007 Cost per airplane Parts 1 Authority for This Rulemaking VerDate Aug<31>2005 Average labor rate per hour Work hours 80 0 Number of U.S.registered airplanes $80, per inspection cycle. 80 ...................... 42 ...................... 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, PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Up to 42 ............ Fleet cost $3,360, per inspection cycle. Up to $3,360. 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 E:\FR\FM\28DER1.SGM 28DER1 Federal Register / Vol. 72, No. 248 / Friday, December 28, 2007 / Rules and Regulations 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, the FAA amends 14 CFR part 39 as follows: I 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 pwalker on PROD1PC71 with RULES 2007–26–07 Boeing: Amendment 39–15309. Docket No. FAA–2007–28352; Directorate Identifier 2007–NM–037–AD. Effective Date (a) This AD becomes effective February 1, 2008. Affected ADs (b) None. VerDate Aug<31>2005 23:53 Dec 27, 2007 Jkt 214001 Applicability (c) This AD applies to Boeing Model 747– 200B, 747–300, 747–400, 747–400D, and 747–400F series airplanes, certificated in any category, equipped with General Electric CF6–80C2 engines. Unsafe Condition (d) This AD results from two reports of missing flipper doors for the engine core cowl. We are issuing this AD to detect and correct migrated hinge pins and damaged flipper doors, which could allow the flipper door to fall off, resulting in the potential for an engine fire to propagate into the flammable leakage zone of the strut and for the amount of fire extinguishing agent reaching the fire to be diluted, and subsequent uncontained fire in the engine strut. 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. Inspection of the Flipper Door Assemblies (f) Within 24 months after the effective date of this AD: Do a general visual inspection for migrated hinge pins and damaged flipper doors of the left- and righthand flipper door assemblies of the engine core cowls, and do all applicable corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–71–2310, dated October 13, 2005. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 18 months for that flipper door assembly, until doing the actions specified in paragraph (g) of this AD. Note 1: Boeing Special Attention Service Bulletin 747–71–2310, dated October 13, 2005, refers to Rohr Service Bulletin TBC/ 80C2–NAC–71–035, dated October 10, 2005, as an additional source of service information for accomplishing the actions specified in paragraph (f) of this AD. Terminating Action for Repetitive Inspections (g) Accomplishing the inspection and applicable modification of a hinge assembly of a flipper door assembly of the engine core cowl in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–71– 2310, dated October 13, 2005; or Rohr Service Bulletin TBC/80C2–NAC–71–035, dated October 10, 2005; terminates the repetitive inspection requirements of this AD for that hinge assembly. Parts Installation (h) As of the effective date of this AD, no person may install, on any airplane, a hinge assembly, part number 224–2335–69, for the flipper door of the engine core cowl unless it has been modified in accordance with the requirements of paragraph (g) of this AD. Material Incorporated by Reference (i) You must use Boeing Special Attention Service Bulletin 747–71–2310, dated October PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 73589 13, 2005, 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/federalregister/cfr/ibr-locations.html. Issued in Renton, Washington, on December 11, 2007. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–24520 Filed 12–27–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE Bureau of Industry and Security 15 CFR Part 772 Definitions of Terms CFR Correction In Title 15 of the Code of Federal Regulations, Parts 300 to 799, revised as of January 1, 2007, on page 577, in § 772.1, in the second column, the second definition of Production is removed. [FR Doc. 07–55526 Filed 12–27–07; 8:45 am] BILLING CODE 1505–01–D DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Parts 201, 312, 314, 601, 610, 801, 807, 809, 812, and 814 [Docket No. 2006N–0466] Exceptions or Alternatives to Labeling Requirements for Products Held by the Strategic National Stockpile AGENCY: Food and Drug Administration, HHS. Interim final rule; request for comments. ACTION: SUMMARY: The Food and Drug Administration (FDA) is issuing regulations to permit FDA Center Directors to grant exceptions or alternatives to certain regulatory labeling requirements applicable to human drugs, biological products, or E:\FR\FM\28DER1.SGM 28DER1

Agencies

[Federal Register Volume 72, Number 248 (Friday, December 28, 2007)]
[Rules and Regulations]
[Pages 73587-73589]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-24520]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28352; Directorate Identifier 2007-NM-037-AD;
Amendment 39-15309; AD 2007-26-07]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-200B, 747-300, 747-
400, 747-400D, and 747-400F Series Airplanes Equipped with General
Electric CF6-80C2 Engines

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 747-200B, 747-300, 747-400, 747-400D, and 747-400F
series airplanes. This AD requires repetitive inspections of the left-
and right-hand flipper door assemblies of the engine

[[Page 73588]]

core cowls for migrated pins and damaged flipper doors, and corrective
actions if necessary. Modification of the hinge assemblies terminates
the repetitive inspections. This AD results from two reports of missing
flipper doors for the engine core cowls. We are issuing this AD to
detect and correct migrated hinge pins and damaged flipper doors, which
could allow the flipper door to fall off, resulting in the potential
for an engine fire to propagate into the flammable leakage zone of the
strut and for the amount of fire extinguishing agent reaching the fire
to be diluted, and subsequent uncontained fire in the engine strut.

DATES: This AD becomes effective February 1, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 1,
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: Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6501; 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
747-200B, 747-300, 747-400, 747-400D, and 747-400F series airplanes.
That NPRM was published in the Federal Register on June 5, 2007 (72 FR
31001). That NPRM proposed to require repetitive inspections of the
left- and right-hand flipper door assemblies of the engine core cowls
for migrated pins and damaged flipper doors, and corrective actions if
necessary. That NPRM specified that the modification of the hinge
assemblies 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 Clarify the Requirements Specified in Paragraph (f) of the
NPRM

Boeing requests that we revise paragraph (f) of the NPRM to clarify
that the modification specified in Boeing Special Attention Service
Bulletin 747-71-2310, dated October 13, 2005, is necessary only if
hinge pins have migrated or flipper doors are damaged or missing.
Boeing states that the instruction to do all applicable corrective
actions could be interpreted to mean that the proposed modification is
required, regardless of the inspection findings.
We agree that modification is necessary only when hinge pins have
migrated or the flipper doors are damaged or missing. Both Boeing
Special Attention Service Bulletin 747-71-2310, and Rohr Service
Bulletin TBC/80C2-NAC-71-035, dated October 10, 2005, clearly state
that modification is necessary only when hinge pins have migrated or
the flipper doors are damaged or missing. We have made no change to the
AD in this regard.

Request to Clarify the Requirements Specified in Paragraph (g) of the
NPRM

Boeing requests that we revise paragraph (g) of the NPRM to clarify
that accomplishing Rohr Service Bulletin TBC/80C2-NAC-71-035, as
instructed in Boeing Special Attention Service Bulletin 747-71-2310,
does not necessarily result in modification of the core cowl. Boeing
points out that, if the hinge pin is properly installed, modification
in accordance with Rohr Service Bulletin TBC/80C2-NAC-71-035 is not
necessary.
We agree with Boeing's comment. The actions specified in Rohr
Service Bulletin TBC/80C2-NAC-71-035 do not require modification if the
hinge pin has not migrated and is properly peened. We have changed
paragraph (g) of this AD to say that accomplishment of the Rohr service
bulletin terminates the repetitive inspection requirements (for non-
discrepant hinge pins) of paragraph (f) of this AD.

Conclusion

We reviewed the relevant data, considered the comments received
from the single commenter, and determined that air safety and the
public interest require adopting the AD with the change described
previously. We also determined that this change will not increase the
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

There are about 297 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average labor Number of U.S.-
Action Work hours rate per hour Parts Cost per airplane registered airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection of flipper door 1 $80 $0 $80, per inspection 42................... $3,360, per
assemblies, per inspection cycle. cycle. inspection cycle.
Modification of hinge assemblies, 1 80 0 80................... Up to 42............. Up to $3,360.
if accomplished.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

[[Page 73589]]

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):

2007-26-07 Boeing: Amendment 39-15309. Docket No. FAA-2007-28352;
Directorate Identifier 2007-NM-037-AD.

Effective Date

(a) This AD becomes effective February 1, 2008.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 747-200B, 747-300, 747-400,
747-400D, and 747-400F series airplanes, certificated in any
category, equipped with General Electric CF6-80C2 engines.

Unsafe Condition

(d) This AD results from two reports of missing flipper doors
for the engine core cowl. We are issuing this AD to detect and
correct migrated hinge pins and damaged flipper doors, which could
allow the flipper door to fall off, resulting in the potential for
an engine fire to propagate into the flammable leakage zone of the
strut and for the amount of fire extinguishing agent reaching the
fire to be diluted, and subsequent uncontained fire in the engine
strut.

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.

Inspection of the Flipper Door Assemblies

(f) Within 24 months after the effective date of this AD: Do a
general visual inspection for migrated hinge pins and damaged
flipper doors of the left- and right-hand flipper door assemblies of
the engine core cowls, and do all applicable corrective actions, by
accomplishing all the actions specified in the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-71-
2310, dated October 13, 2005. Do all applicable corrective actions
before further flight. Repeat the inspection thereafter at intervals
not to exceed 18 months for that flipper door assembly, until doing
the actions specified in paragraph (g) of this AD.

Note 1: Boeing Special Attention Service Bulletin 747-71-2310,
dated October 13, 2005, refers to Rohr Service Bulletin TBC/80C2-
NAC-71-035, dated October 10, 2005, as an additional source of
service information for accomplishing the actions specified in
paragraph (f) of this AD.

Terminating Action for Repetitive Inspections

(g) Accomplishing the inspection and applicable modification of
a hinge assembly of a flipper door assembly of the engine core cowl
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 747-71-2310, dated October 13, 2005; or
Rohr Service Bulletin TBC/80C2-NAC-71-035, dated October 10, 2005;
terminates the repetitive inspection requirements of this AD for
that hinge assembly.

Parts Installation

(h) As of the effective date of this AD, no person may install,
on any airplane, a hinge assembly, part number 224-2335-69, for the
flipper door of the engine core cowl unless it has been modified in
accordance with the requirements of paragraph (g) of this AD.

Material Incorporated by Reference

(i) You must use Boeing Special Attention Service Bulletin 747-
71-2310, dated October 13, 2005, 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/cfr/ibr-locations.html.

Issued in Renton, Washington, on December 11, 2007.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-24520 Filed 12-27-07; 8:45 am]
BILLING CODE 4910-13-P

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