Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations 67445 

Effective Date 

(l) This amendment becomes effective on 

December 27, 2006. 

Issued in Renton, Washington, on 

November 8, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E6–19535 Filed 11–21–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24877; Directorate 

Identifier 2005–NM–253–AD; Amendment 

39–14831; AD 2006–24–02] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–200B, 

747–200C, 747–200F, 747SR, and 

747SP Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

747 series airplanes. That AD currently 

requires repetitive inspections to detect 

cracks at certain stringer fastener 

locations; and repair, if necessary. For 

certain airplanes, that AD requires a 

modification in certain areas where 

reports indicate that cracking was 

prevalent. This modification terminates 

the repetitive inspections only for those 

areas, and is also an option for other 

airplanes affected by the existing AD. 

This new AD requires an additional 

inspection of areas that may have 

Alodine-coated rivets installed, and 

repair if necessary. This AD results from 

a report of cracking discovered in a skin 

lap joint that was previously inspected 

using the eddy current method. We are 

issuing this AD to prevent rapid 

decompression of the airplane due to 

disbonding and subsequent cracking of 

the skin panels. 

DATES: This AD becomes effective 

December 27, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 27, 2006. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

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 service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://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 

supersedes AD 90–26–10, amendment 

39–6836 (55 FR 51401, December 14, 

1990). The existing AD applies to 

certain Boeing Model 747 series 

airplanes. That NPRM was published in 

the Federal Register on May 25, 2006 

(71 FR 30074). That NPRM proposed to 

continue to require repetitive 

inspections to detect cracks at certain 

stringer fastener locations, and repair if 

necessary. For certain airplanes, that 

NPRM proposed to continue to require 

modification in certain areas where 

reports indicate that cracking was 

prevalent. This modification terminates 

the repetitive inspections only for those 

areas, and is also an option for other 

airplanes affected by the existing AD. 

That NPRM also proposed to require an 

additional inspection of areas that may 

have Alodine-coated rivets installed, 

and repair if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Support for the NPRM 

Boeing supports the NPRM. 

Request To Recognize Overlapping 

Inspections 

The Air Transport Association, on 

behalf of one of its members, Northwest 

Airlines, requests that we recognize that 

a service bulletin currently in 

development could result in 

overlapping inspections and cause 

duplication of efforts. Northwest 

Airlines states that it has been advised 

by Boeing that the service bulletin in 

development will recommend external 

detailed inspections and/or external 

surface high frequency eddy current 

inspections in a good portion of the 

region affected by the NPRM. This new 

service bulletin resulted from a recent 

report of skin cracking in section 41. 

We partially agree with the 

commenters. We agree that it is 

important to avoid duplication of effort. 

However, because the service bulletin 

that the commenters mention has not 

been issued, we have not issued an 

NPRM for the subject of that service 

bulletin. When the service bulletin is 

issued, we will review it and any 

forthcoming proposed rule in an effort 

to prevent duplication of tasks. We 

consider that to delay this AD action 

would be inappropriate, since we have 

determined that an unsafe condition 

exists and that replacement of certain 

parts must be accomplished to ensure 

continued safety. We have not changed 

the AD in this regard. 

Explanation of Editorial Changes 

We have clarified the Summary 

section of this AD to state that this new 

AD requires ‘‘an additional inspection’’

rather than a one-time inspection at a 

reduced threshold. The new inspection 

required by this AD is ‘‘additional’’ and, 

therefore, we are not reducing a 

threshold in the previous AD. 

We have also removed the words, ‘‘at 

intervals not to exceed 150 flight 

cycles’’ from paragraph (k)(1)(i) of this 

AD because it duplicates information 

already in paragraph (k)(1) of this AD, 

and may cause confusion. 

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. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. There are about 

132 airplanes of the affected design in 

the worldwide fleet. This AD affects 

about 59 airplanes of U.S. registry. The 

average labor rate is $80 per work hour. 

mstockstill on PROD1PC61 with RULES

67446 Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane Fleet cost 

Inspection (required by AD 90–26–10) ............... 48 None ........... $3,840, per inspection 

cycle.

$226,560, per inspection cycle. 

Modification (required by AD 90–26–10) ............ 620 $69,246 ....... $118,846 ...................... $7,011,914. 

Inspection (new action) ....................................... 48 None ........... $3,840, per inspection 

cycle.

$226,560, 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 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

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: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–6836 (55 

FR 51401, December 14, 1990) and by 

adding the following new airworthiness 

directive (AD): 

2006–24–02 Boeing: Amendment 39–14831. 

Docket No. FAA–2006–24877; 

Directorate Identifier 2005–NM–253–AD. 

Effective Date 

(a) This AD becomes effective December 

27, 2006. 

Affected ADs 

(b) This AD supersedes AD 90–26–10. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, 747–100B, 747–200B, 747–200C, 747–

200F, 747SR, and 747SP series airplanes, 

certificated in any category; line numbers 001 

through 430 inclusive. 

Unsafe Condition 

(d) This AD results from a report of 

cracking discovered in a skin lap joint that 

was previously inspected using the eddy 

current method. We are issuing this AD to 

prevent rapid decompression of the airplane 

due to disbonding and subsequent cracking 

of the skin panels. 

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. 

Restatement of Certain Requirements of AD 

90–26–10 

Inspections 

(f) Prior to the accumulation of 12,000 

flight cycles or within the next 1,000 flight 

cycles after January 22, 1991 (the effective 

date of AD 90–26–10), whichever occurs 

later, unless previously accomplished within 

the last 1,000 flight cycles, conduct an 

external detailed and external high frequency 

eddy current (HFEC) inspection for cracks of 

the fuselage skin from body station (BS) 220 

to BS 520, left- and right-hand sides of the 

airplane between stringers (S)–6 and S–14, 

excluding the skin lap joints, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2321, 

dated October 31, 1989; or Revision 7, dated 

October 27, 2005. After the effective date of 

this AD, only Revision 7 may be used. Doing 

the inspections in this paragraph in 

accordance with Revision 7 of the service 

bulletin eliminates the need for doing the 

actions in paragraph (k) of this AD. Repeat 

the inspections thereafter at intervals not to 

exceed 2,000 flight cycles until the 

terminating modification in paragraph (g) of 

this AD is done, except as provided by 

paragraph (h) of this AD. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Terminating Modification 

(g) For airplanes line numbers 001 through 

200 inclusive, prior to the accumulation of 

20,000 total flight cycles, or within 48 

months after the January 22, 1991, whichever 

occurs later: Perform the terminating 

modification of the skin panel from BS 340 

to BS 520, S–6 to S–14, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2321, dated 

October 31, 1989; or Revision 7, dated 

October 27, 2005. After the effective date of 

this AD, only Revision 7 may be used. The 

modification consists of replacing the skin 

panel with a new skin panel which was 

manufactured utilizing the improved hot 

phosphoric acid anodize bonding process. 

(h) Replacement of the skin panel required 

by paragraph (g) of this AD constitutes 

terminating action for the inspections from 

BS 340 to BS 520 required by paragraphs (f) 

and (k) of this AD. The inspections from BS 

220 to BS 340 required by paragraph (f) of 

this AD are to be continued. 

Adjustments for Cabin Differential Pressure 

(i) Before the effective date of this AD: 

Flight cycles conducted at 2.0 pounds per 

square inch (psi) or less cabin differential 

pressure need not be counted for the purpose 

of this airworthiness directive. 

(j) Before the effective date of this AD: For 

Model 747SR airplanes only, the threshold 

mstockstill on PROD1PC61 with RULES

Federal Register / Vol. 71, No. 225 / Wednesday, November 22, 2006 / Rules and Regulations 67447 

and repetitive inspection intervals specified 

herein may be multiplied by the 1.2 

adjustment factor based on continued mixed 

operation at lower cabin pressure 

differentials. 

New Requirements of This AD 

Additional Inspection of Skins With 

Alodine-Coated Rivets 

(k) For airplanes identified in Figure 9 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2321, 

Revision 7, dated October 27, 2005, as 

requiring additional inspection: Within 150 

flight cycles after the effective date of this 

AD, do the inspection in paragraph (k)(1) or 

(k)(2) of this AD in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

(1) Do an external detailed inspection for 

cracking of Area 1, and repeat the inspection 

thereafter at intervals not to exceed 150 flight 

cycles until one of the actions in paragraph 

(k)(1)(i), (k)(1)(ii), or (k)(1)(iii) is 

accomplished. Repeat the inspection of Area 

1 thereafter in accordance with the 

requirements of paragraph (f) of this AD. 

(i) The inspection in accordance with 

paragraph (k)(1) of this AD has been done 

seven times. If this option is used: Within 

150 flight cycles after the seventh inspection, 

do the inspection required by paragraph 

(k)(2) of this AD. 

(ii) The inspection in accordance with 

paragraph (k)(2) has been accomplished. 

(iii) The inspections in accordance with 

paragraph (f) of this AD has been 

accomplished once in accordance with 

Revision 7 of the service bulletin. 

(2) Do an external HFEC inspection for 

cracking of Area 1 in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2321, Revision 7, 

dated October 27, 2005. Repeat the 

inspection of Area 1 thereafter in accordance 

with the requirements of paragraph (f) of this 

AD. 

Repair 

(l) If any crack is found during any 

inspection required by this AD: Before 

further flight, repair in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2321, dated October 

31, 1989; or Revision 7, dated October 27, 

2005. After the effective date of this AD, only 

Revision 7 of the service bulletin may be 

used. Where Revision 7 of the service 

bulletin specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD. 

Adjustments to Compliance Time: Cabin 

Differential Pressure 

(m) For the purposes of calculating the 

compliance threshold and repetitive interval 

for actions required by paragraphs (f), (g), and 

(k) of this AD, on or after the effective date 

of this AD: All flight cycles, including the 

number of flight cycles in which cabin 

differential pressure is at 2.0 psi or less, must 

be counted when determining the number of 

flight cycles that have occurred on the 

airplane, and a 1.2 adjustment factor may not 

be used. However, for airplanes on which the 

repetitive interval for the actions required by 

paragraphs (f) and (k) of this AD have been 

calculated in accordance with paragraph (i) 

or (j) of this AD by excluding the number of 

flight cycles in which cabin differential 

pressure is at 2.0 pounds psi or less, or by 

using a 1.2 adjustment factor: Continue to 

adjust the repetitive interval in accordance 

with paragraph (i) or (j) of this AD until the 

next inspections required by paragraph (f) or 

(k) of this AD are accomplished. Thereafter, 

no adjustment to compliance times based on 

paragraph (i) or (j) of this AD is allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(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. 

(4) AMOCs approved previously in 

accordance with AD 90–26–10 are acceptable 

for compliance with the requirements of this 

AD, provided that any alternative terminating 

action was not based upon inspection results 

using sliding probe low-frequency eddy 

current (LFEC), sliding probe HFEC, or midfrequency eddy current (MFEC) inspection 

method; and provided that any alternative 

method future inspections did not 

incorporate sliding probe LFEC or MFEC 

inspection method. 

Material Incorporated by Reference 

(o) You must use Boeing Alert Service 

Bulletin 747–53A2321, dated October 31, 

1989; and Boeing Alert Service Bulletin 747–

53A2321, Revision 7, dated October 27, 2005; 

as applicable; to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. (Only the first page of Boeing 

Alert Service Bulletin 747–53A2321, dated 

October 31, 1989, contains the document 

issue date; no other page of this document 

contains this information.) 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 

http://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 

http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

November 8, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E6–19534 Filed 11–21–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

National Oceanic and Atmospheric 

Administration 

15 CFR Part 902 

50 CFR Part 622 

[Docket No. 060731206–6280–02; I.D. 

072806A] 

RIN 0648–AS67 

Fisheries of the Caribbean, Gulf of 

Mexico, and South Atlantic; Reef Fish 

Fishery of the Gulf of Mexico; 

Amendment 26 

AGENCY: National Marine Fisheries 

Service (NMFS), National Oceanic and 

Atmospheric Administration (NOAA), 

Commerce. 

ACTION: Final rule. 

SUMMARY: NMFS issues this final rule to 

implement Amendment 26 to the 

Fishery Management Plan for the Reef 

Fish Fishery of the Gulf of Mexico 

(FMP). Amendment 26 establishes an 

individual fishing quota (IFQ) program 

for the commercial red snapper sector of 

the reef fish fishery in the Gulf of 

Mexico. Initial participants in the IFQ 

program will receive percentage shares 

of the commercial quota of red snapper 

based on specified historical landings 

criteria. The percentage shares of the 

commercial quota will equate to annual 

IFQ allocations. Both shares and IFQ 

allocations will be transferable. In 

addition, NMFS informs the public of 

the approval by the Office of 

Management and Budget (OMB) of the 

collection-of-information requirements 

contained in this final rule and 

publishes the OMB control numbers for 

those collections. The intended effect of 

this rule is to manage the commercial 

red snapper sector of the reef fish 

fishery to preserve its long-term 

economic viability and to achieve 

optimum yield from the fishery. 

DATES: This rule is effective January 1, 

2007, except: Amendments to 

mstockstill on PROD1PC61 with RULES