Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55519 

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 adding the following new 

airworthiness directive (AD): 

2005–19–21 Airbus: Amendment 39–14286. 

Docket No. FAA–2005–22484; 

Directorate Identifier 2003–NM–270–AD. 

Effective Date 

(a) This AD becomes effective October 7, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Airbus airplanes, 

certificated in any category, listed in Table 1 

of this AD. 

TABLE 1.—APPLICABILITY

Airbus model— As identified in Airbus service bulletin— 

A330–202, –223, –243, and –343 airplanes .............................................................. A330–56–3006, Revision 01, dated March 24, 2003. 

A340–313 airplanes .................................................................................................... A340–56–4006, Revision 01, dated March 24, 2003. 

Unsafe Condition 

(d) This AD results from a report indicating 

that, during production, the windshield 

central retainer may have been installed with 

attachment bolts that were too short, which 

prevented the thread of the bolt from fully 

engaging in the self-locking nut. We are 

issuing this AD to prevent loosened 

attachment bolts, which could result in loss 

of the windshield and consequent reduced 

structural integrity 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. 

Inspection 

(f) Within 6 months after the effective date 

of this AD, perform a detailed inspection of 

the windshield central retainer for 

discrepancies of the attachment bolts, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

56–3006 or A340–56–4006, both excluding 

Appendix 01, Revision 01, dated March 24, 

2003; as applicable. If the protrusion of any 

attachment bolt is not within the limits 

specified in the service bulletin, replace the 

bolt and corresponding nut with new parts 

before further flight in accordance with the 

service bulletin. 

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.’’

Modification According to Previous Issue of 

Service Bulletin 

(g) Inspecting the windshield central 

retainer, and doing applicable corrective 

actions, is also acceptable for compliance 

with the requirements of paragraph (f) of this 

AD if done before the effective date of this 

AD in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

56–3006 or A340–56–4006, both dated March 

12, 2003; as applicable. 

No Reporting Requirement 

(h) Although Airbus Service Bulletins 

A330–56–3006 and A340–56–4006 specify 

sending an inspection report to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

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 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(j) French airworthiness directives 2003–

123(B) R1 and 2003–124(B) R1, both dated 

April 16, 2003, also address the subject of 

this AD. 

Material Incorporated by Reference 

(k) To perform the actions that are required 

by this AD, unless the AD specifies 

otherwise, you must use Airbus Service 

Bulletin A330–56–3006, excluding Appendix 

01, Revision 01, dated March 24, 2003; or 

Airbus Service Bulletin A340–56–4006, 

excluding Appendix 01, Revision 01, dated 

March 24, 2003; as applicable. 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 Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, 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 

September 13, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18782 Filed 9–21–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21355; Directorate 

Identifier 2005–NM–037–AD; Amendment 

39–14288; AD 2005–19–23] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F Series 

Airplanes Powered by General Electric 

or Pratt & Whitney Engines 

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 

767 series airplanes. That AD currently 

requires repetitive inspections to detect 

discrepancies of the eight aft-most 

fastener holes in the horizontal tangs of 

the midspar fitting of the strut, and 

corrective actions if necessary. That AD 

also provides an optional terminating 

action for the repetitive inspections. 

55520 Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 

This new AD adds repetitive 

inspections for cracks of the closeout 

angle that covers the two aft-most 

fasteners in the lower tang of the 

midspar fitting, and related investigative 

and corrective actions if necessary. This 

AD also reduces the inspection interval 

of the upper tang of the outboard 

midspar fitting; and provides an 

optional terminating action for the 

repetitive inspections. This AD results 

from a report of a crack in a closeout 

angle that covers the two aft-most 

fasteners in the lower tang of the 

midspar fitting; and the discovery of a 

crack in the lower tang of the midspar 

fitting under the cracked closeout angle. 

We are issuing this AD to prevent 

fatigue cracking in the primary strut 

structure and reduced structural 

integrity of the strut, which could result 

in separation of the strut and engine. 

EFFECTIVE DATE: This AD becomes 

effective October 27, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of Boeing Alert Service Bulletin 767–

54A0101, Revision 4, dated February 10, 

2005, listed in the AD as of October 27, 

2005. 

On June 9, 2004 (69 FR 24947, May 

5, 2004), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Service Bulletin 

767–54A0101, Revision 3, dated 

September 5, 2002. 

On May 15, 2001 (66 FR 18523, April 

10, 2001), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Service Bulletin 

767–54A0101, Revision 1, dated 

February 3, 2000. 

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: 

Candice Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; 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 2004–09–14, amendment 

39–13603 (69 FR 24947, May 5, 2004). 

The existing AD applies to certain 

Model 767 series airplanes. That NPRM 

was published in the Federal Register 

on June 3, 2005 (70 FR 32527). That 

NPRM proposed to continue to require 

repetitive inspections to detect 

discrepancies of the eight aft-most 

fastener holes in the horizontal tangs of 

the midspar fitting of the strut, and 

corrective actions if necessary. That 

NPRM also proposed to require 

repetitive inspections for cracks of the 

closeout angle that covers the two aftmost fasteners in the lower tang of the 

midspar fitting, and related investigative 

and corrective actions if necessary. That 

NPRM also proposed to reduce the 

inspection interval of the upper tang of 

the outboard midspar fitting; and to 

provide an optional terminating action 

for 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 Remove Airplane Reference 

From Applicability 

The airplane manufacturer requests 

that we remove the reference to Boeing 

Model 767–400ER series airplanes from 

the applicability of the NPRM. The 

commenter points out that these 

airplanes have improved corrosion 

resistant steel (CRES) mid-spar fittings. 

We agree with the commenter. The 

Model 767–400ER series airplanes are 

not included in the effectivity of the 

Boeing Alert Service Bulletin 767–

54A0101, Revision 4, dated February 10, 

2005 (which was cited as the 

appropriate source of service 

information for doing the actions in the 

NPRM), but were inadvertently 

included in the applicability of the 

NPRM. We have changed the final rule 

to remove this model designation from 

the applicability. 

Request To Include Inspection 

Requirements for Airplanes With CRES 

Repair Strap 

The same commenter points out that 

some airplanes have had the closeout 

angle previously repaired by the 

addition of a CRES repair strap. This 

repair strap covers two aft-most bolts of 

the closeout angle at the midspar fitting. 

The commenter states that the repair 

strap prevents high-frequency eddy 

current inspections of the closeout 

angle. The commenter requests that the 

final rule include inspection 

requirements for these airplanes. 

We partially agree with the 

commenter. We agree that additional 

inspections may be required for these 

airplanes. We disagree with including 

inspection requirements for these 

airplanes in the final rule. In accordance 

with 14 CFR 39.17, if the original 

airplane configuration is altered, 

modified, or repaired in any way that 

may affect the ability to accomplish the 

actions of an AD, the operator should 

apply for an alternative method of 

compliance (AMOC) through the FAA. 

Information about AMOCs is included 

in paragraph (q) of the final rule. We 

have not changed the final rule in this 

regard. 

Explanation of Change Made to 

Paragraph (i) 

We have simplified paragraph (i) of 

the final rule by referring to the 

‘‘Alternative Methods of Compliance 

(AMOCs)’’ paragraph of this AD for 

repair methods. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

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. 

Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55521 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.-registered airplanes 

Fleet cost 

Option 1: Detailed inspection (required by AD 2004–09–14).1 $65 None ...... $65, per inspection cycle.263 N/A (depends on chosen option). 

Option 2: HFEC inspection (required by AD 2004–09–14).3 $65 None ...... $195, per inspection cycle.263 N/A (depends on chosen option). 

HFEC inspection (new proposed 

action).

4 $65 None ...... $260, per inspection cycle.263 $68,380, 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 39–13603 (69 

FR 24947, May 5, 2004) and by adding 

the following new airworthiness 

directive (AD): 

2005–19–23 Boeing: Amendment 39–14288. 

Docket No. FAA–2005–21355; 

Directorate Identifier 2005–NM–037–AD. 

Effective Date 

(a) This AD becomes effective October 27, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2004–09–14. 

Applicability 

(c) This AD applies to Boeing Model 767–

200, –300, and –300F series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 767–54A0101, 

Revision 4, dated February 10, 2005. 

Unsafe Condition 

(d) This AD was prompted by a report of 

a crack in a closeout angle that covers the 

two aft-most fasteners in the lower tang of the 

midspar fitting; and the discovery of a crack 

in the lower tang of the midspar fitting under 

the cracked closeout angle. We are issuing 

this AD to prevent fatigue cracking in the 

primary strut structure and reduced 

structural integrity of the strut, which could 

result in separation of the strut and engine. 

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 Requirements of AD 2004–

09–14 

Repetitive Inspections 

(f) Except as provided by paragraph (g) of 

this AD, before the accumulation of 10,000 

total flight cycles, or within 600 flight cycles 

after May 15, 2001 (the effective date of AD 

2001–07–05, amendment 39–12170), 

whichever occurs later: Accomplish the 

inspections required by paragraph (f)(1) or 

(f)(2) of this AD, as applicable. 

(1) Perform a detailed inspection of the 

four aft-most fastener holes in the horizontal 

tangs of the midspar fitting of the strut to 

detect cracking, in accordance with Part 1, 

‘‘Detailed Inspection,’’ of the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–54A0101, Revision 1, 

dated February 3, 2000. If no cracking is 

detected, repeat the inspection thereafter at 

the applicable intervals specified in Table 1, 

‘‘Reinspection Intervals for Part 1—Detailed 

Inspection’’ included in Figure 1 of the 

service bulletin. 

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.’’

(2) Perform a high frequency eddy current 

(HFEC) inspection of the four aft-most 

fastener holes in the horizontal tangs of the 

midspar fitting of the strut to detect 

discrepancies (cracking, incorrect fastener 

hole diameter), in accordance with Part 2, 

‘‘High Frequency Eddy Current (HFEC) 

Inspection,’’ of the Accomplishment 

Instructions of the service bulletin. 

Accomplish the requirements specified in 

paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as 

applicable; and repeat the inspection 

thereafter at the applicable intervals specified 

in Table 2, ‘‘Reinspection Intervals for Part 

2—HFEC Inspection’’ included in Figure 1 of 

the service bulletin. 

(i) If no cracking is detected and the 

fastener hole diameter is less than or equal 

to 0.5322 inch, before further flight, rework 

the hole in accordance with Part 3 of the 

Accomplishment Instructions of the service 

bulletin. 

55522 Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 

(ii) If no cracking is detected and the 

fastener hole diameter is greater than 0.5322 

inch, before further flight, accomplish the 

requirements specified in either paragraph 

(h)(1) or (h)(2) of this AD. 

(g) For airplanes on which the two aft-most 

fasteners have been inspected in accordance 

with Boeing Service Bulletin 767–54A0101, 

Revision 1, dated February 3, 2000, prior to 

May 15, 2001: Perform the initial inspection 

of the four aft-most fasteners in accordance 

with paragraph (f) of this AD before the 

accumulation of 10,000 total flight cycles, or 

within 1,500 flight cycles after May 15, 2001, 

whichever occurs later. 

Corrective Actions 

(h) If any cracking is detected after 

accomplishment of any inspection required 

by paragraph (f) of this AD, before further 

flight, accomplish the requirements specified 

in either paragraph (h)(1) or (h)(2) of this AD. 

(1) Accomplish the terminating action 

specified in Part 4 of the Accomplishment 

Instructions of Boeing Service Bulletin 767–

54A0101, Revision 1, dated February 3, 2000; 

Boeing Service Bulletin 767–54A0101, 

Revision 3, dated September 5, 2002; or 

Boeing Alert Service Bulletin 767–54A0101, 

Revision 4, dated February 10, 2005. 

Accomplishment of this paragraph 

terminates the requirements of this AD. After 

the effective date of this AD, only Boeing 

Alert Service Bulletin 767–54A0101, 

Revision 4, may be used. 

(2) Replace the midspar fitting of the strut 

with a serviceable part, or repair in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. Repeat the applicable 

inspection thereafter at the applicable time 

specified in paragraph (f)(1) or (f)(2) of this 

AD. 

(i) If any discrepancies (cracking, incorrect 

fastener hole diameter) are detected during 

any inspection required by paragraph (f) or 

(p) of this AD, for which the service bulletin 

specifies that the manufacturer may be 

contacted for disposition of those repair 

conditions: Before further flight, accomplish 

the applicable related investigative and 

corrective actions (including fastener hole 

rework and/or midspar fitting replacement) 

using a method approved in accordance with 

the procedures specified in paragraph (q) of 

this AD. 

Additional Inspections 

(j) Prior to the accumulation of 10,000 total 

flight cycles, or within 600 flight cycles after 

June 9, 2004 (the effective date of AD 2004–

09–14), whichever occurs later: Perform the 

inspections specified in paragraph (f)(1) or 

(f)(2) of this AD, as applicable, on all eight 

aft-most fastener holes or the four forward 

fastener holes in the group of eight aft-most 

fastener holes not inspected per paragraph 

(f)(1), (f)(2), or (g) of this AD. The inspection 

must be done per the Accomplishment 

Instructions in Boeing Service Bulletin 767–

54A0101, Revision 3, dated September 5, 

2002; or Boeing Alert Service Bulletin 767–

54A0101, Revision 4, dated February 10, 

2005. Accomplishment of the applicable 

inspection on all eight aft-most fastener holes 

constitutes terminating action for the 

repetitive inspection requirements of 

paragraphs (f)(1), (f)(2), and (g) of this AD. 

(k) If no cracking or discrepancy is 

detected during any detailed inspection 

required by paragraph (j) of this AD, repeat 

the inspections of all eight aft-most fastener 

holes thereafter at the applicable intervals 

specified in Table 1 of this AD. 

(l) If no cracking or discrepancy is detected 

during any HFEC inspection required by 

paragraph (j) of this AD or by this paragraph 

of this AD: Perform the follow-on actions 

specified in paragraph (f)(2)(i) or (f)(2)(ii) of 

this AD, as applicable, per the 

Accomplishment Instructions in Boeing 

Service Bulletin 767–54A0101, Revision 3, 

dated September 5, 2002; or Boeing Alert 

Service Bulletin 767–54A0101, Revision 4, 

dated February 10, 2005; and repeat the 

inspections of all eight aft-most fastener 

holes thereafter at the applicable intervals 

specified in Table 1 of this AD. 

TABLE 1.—REPETITIVE INSPECTION INTERVALS FOR ALL EIGHT AFT-MOST FASTENER HOLES

If— Repetitive intervals—

(1) All eight aft-most fastener holes were inspected per paragraph (j) of this AD:.At the applicable intervals specified in Table 1, ‘‘Reinspection Intervals for Part 1,’’ or Table 2, 

‘‘Reinspection Intervals for Part 2,’’ as applicable. Both tables are included in Figure 1 of the 

applicable service bulletin. 

Within 1,500 flight cycles after the effective date of this AD, only the repetitive intervals in Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005, may be used. 

(2) Only the four forward fastener holes in the 

group of eight aft-most fastener holes were 

inspected per paragraph (j) of this AD:.

At the next scheduled repetitive inspection required by paragraph (f)(1) of (f)(2) of this AD, as 

applicable. Thereafter at the applicable intervals specified in Table 1, ‘‘Reinspection Intervals 

for Part 1,’’ or Table 2, ‘‘Reinspection Intervals for Part 2,’’ as applicable. Both tables are included in Figure 1 of the applicable service bulletin. 

Within 1,500 flight cycles after the effective date of this AD, only the repetitive intervals in Boeing Alert Service Bulletin 767–54A0101, Revision 4, dated February 10, 2005, may be used. 

Corrective Actions for Discrepancies 

(m) If any cracking or discrepancy is 

detected during any inspection required by 

paragraphs (j), (k), or (l) of this AD, before 

further flight: Accomplish the corrective 

actions described in paragraph (h) of this AD, 

except as provided in paragraph (i) of this 

AD. 

Service Bulletin Revisions 

(n) Accomplishing the terminating action 

in paragraph (h)(1) of this AD before June 9, 

2004, in accordance with the service bulletin 

revisions in Table 2 of this AD, is acceptable 

for compliance with the requirements of this 

AD. After the effective date of this AD, only 

Boeing Alert Service Bulletin 767–54A0101, 

Revision 4, dated February 10, 2005, may be 

used for accomplishing the terminating 

action in paragraph (h)(1) of this AD. 

TABLE 2.—SERVICE BULLETINS FOR TERMINATING ACTION

Service bulletin Revision Date 

Boeing Alert Service Bulletin 767–54A0101 ............................................................................................ Original ......... September 23, 1999. 

Boeing Service Bulletin 767–54A0101 ..................................................................................................... 2 ................... January 10, 2002. 

Inspections Accomplished per Previous 

Issues of Service Bulletin 

(o) Inspections required by paragraphs (f) 

and (g) of this AD that are accomplished 

before June 9, 2004, in accordance with the 

service bulletin revisions in Table 3 of this 

AD are considered acceptable for compliance 

with the corresponding action specified in 

this AD. 

Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55523 

TABLE 3.—SERVICE BULLETINS FOR PREVIOUSLY ACCOMPLISHED INSPECTIONS

Boeing service bulletin Revision Date 

Boeing Service Bulletin 767–54A0101 ........................................................................................................ 2 January 10, 2002. 

Boeing Service Bulletin 767–54A0101 ........................................................................................................ 3 September 5, 2002. 

Boeing Alert Service Bulletin 767–54A0101 ............................................................................................... 4 February 10, 2005. 

New Requirements of This AD 

Inspections of Closeout Angle and Corrective 

Action 

(p) For airplanes for which the 

‘‘Reinspection Intervals for Part 1,’’

referenced in Table 1 of paragraph (l) of this 

AD apply: At the next applicable inspection, 

do an HFEC inspection for cracks of the 

closeout angle that covers the two aft-most 

fasteners in the lower tang of the midspar 

fitting and any related investigative and 

corrective actions, by doing all the applicable 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–54A0101, Revision 4, dated February 10, 

2005. Repeat the inspection at the applicable 

interval in Table 1, ‘‘Reinspection Intervals 

for Part 1,’’ in Figure 1 of the alert service 

bulletin. 

Note 2: Boeing Alert Service Bulletin 767–

54A0101, Revision 4, dated February 10, 

2005, refers to the Boeing service bulletins in 

the Table 4 of this AD as additional sources 

of service information for doing the 

terminating action in paragraph (h)(1) of this 

AD. 

TABLE 4.—ADDITIONAL SOURCES OF SERVICE INFORMATION

Boeing service bulletin Revision level Date Title 

767–54–0052 ............. Original ......... June 11, 1992 .............................. Nacelles/Pylons—Strut—Aft Lower Spar—Fastener Corrosion—Inspection and Replacement. 

767–54–0061 ............. 2 ................... November 23, 1999 ..................... Nacelles/Pylons—Wing-to-Strut Attach Fittings—Lower Spar Bushing Inspection and Replacement. 

767–54–0069 ............. 2 ................... August 31, 2000 .......................... Nacelles/Pylons—Midspar Fitting—Underwing Sideload Fitting—

Fuse Pin Replacement and Wing Rework. 

767–54–0072 ............. Original ......... March 13, 1997 ............................ Nacelles/Pylons—Strut Attach Upper Link—Upper Link Inspection, 

Rework or Replacement. 

767–54–0074 ............. Original ......... March 27, 1997 ............................ Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement. Where this service bulletin refers to a cotter pin with part number (P/N) MS25665–374, the P/N should be 

MS24665–374. Where this service bulletin says, ‘‘If no crack indication is found, reinstall the fuse pin,’’ the correct statement is 

‘‘If no crack indication is found, continue to Step F.’’

767–54–0080 ............. 1 ................... May 9, 2002 ................................. Nacelles/Pylons—Pratt and Whitney Powered Airplanes—Nacelle 

Strut and Wing Structure Modification. 

767–54–0081 ............. 1 ................... February 7, 2002 ......................... Nacelles/Pylons—General Electric Powered Airplanes—Nacelle 

Strut and Wing Structure Modification. 

767–54A0062 ............. 5 ................... November 11, 2002 ..................... Nacelles/Pylons—Strut Attach Fuse Pins—Midspar Fuse Pin Inspection and Replacement. 

767–54A0094 ............. 2 ................... February 7, 2002 ......................... Nacelles/Pylons—Strut-to-Wing Attachment—Diagonal Brace Inspection/Rework/Replacement. 

767–57–0063 ............. 1 ................... November 30, 2000 ..................... Wings—Side Load Underwing Fitting—Inspection/Rework. 

Note 3: Certain service bulletins referenced 

in Table 4 of this AD are related to the ADs 

listed in Table 5 of this AD. 

TABLE 5.—OTHER RELEVANT RULEMAKING

AD Applicability Related Boeing service 

bulletin AD requirement 

AD 94–11–02, amendment 39–

8918, (59 FR 27229, May 

26, 1994).

All Boeing Model 767 series 

airplanes.

767–54A0062 ......................... Repetitive detailed visual and eddy current 

inspections to detect cracks of certain 

midspar fuse pins, and replacement of any 

cracked midspar fuse pin with a new fuse 

pin. 

AD 99–07–06, amendment 39–

11091 (64 FR 14578, March 

26, 1999).

Certain Boeing Model 767 series airplanes.767–54A0094 ......................... Repetitive inspections to detect cracking or 

damage of the forward and aft lugs of the 

diagonal brace of the nacelle strut; followon actions, if necessary; and an optional 

terminating action for the repetitive inspections. Superseded by AD 2000–07–05. 

AD 2000–07–05, amendment 

39–11659 (65 FR 18883, 

April 10, 2000).

Certain Boeing Model 767 series airplanes.767–54A0094 ......................... Requires the previously optional terminating 

action of AD 99–07–06. 

55524 Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 

TABLE 5.—OTHER RELEVANT RULEMAKING—Continued 

AD Applicability Related Boeing service 

bulletin AD requirement 

AD 2000–10–51, amendment 

39–11770 (65 FR 37011, 

June 13, 2000).

Certain Boeing Model 767 series airplances.767–54–0074 .......................... One-time inspection to determine whether 

certain bolts are installed in the side load 

underwing fittings on both struts, and various follow-on actions, if necessary. 

AD 2001–02–07, amendment 

39–12091 (66 FR 8085, January 29, 2001).

Certain Boeing Model 767 series airplanes powered by 

Pratt & Whitney engines.

767–54–0069, 767–54–0080, 

and 767–54–0094.

Modification of the nacelle strut and wing 

structure. Terminates certain requirements 

of AD 94–11–02. 

AD 2001–06–12, amendment 

39–12159 (66 FR 17492, 

April 2, 2001).

Certain Boeing Model 767 series airplanes powered by 

General Electric engines.

767–54–0069, 767–54–0081, 

and 767–54–0094.

Modification of the nacelle strut and wing 

structure. Terminates certain requirements 

of AD 94–11–02. 

AD 2003–03–02, amendment 

39–13026 (68 FR 4374, January 29, 2003).

All Boeing Model 767 series 

airplanes.

767–54A0062 ......................... Supersedes AD 94–11–02; Retains all requirements but reduces certain compliance 

times for certain inspections, expands the 

detailed and eddy current inspections, and 

limits the applicability. 

Alternative Methods of Compliance (AMOCs) 

(q)(1) The Manager, Seattle 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) AMOCs approved previously according 

to AD 2004–09–14, amendment 39–13603, 

are approved as AMOCs for the 

corresponding requirements of this AD. 

(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. 

(4) 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. 

Material Incorporated by Reference 

(r) You must use the service information 

identified in Table 6 of this AD to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. 

TABLE 6.—MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision 

level Date 

Boeing Service Bulletin 767–54A0101 ........................................................................................................ 1 February 3, 2000. 

Boeing Service Bulletin 767–54A0101 ........................................................................................................ 3 September 5, 2002. 

Boeing Alert Service Bulletin 767–54A0101 ............................................................................................... 4 February 10, 2005. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 767–54A0101, 

Revision 4, dated February 10, 2005, in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) On June 9, 2004 (69 FR 24947, May 5, 

2004), the Director of the Federal Register 

approved the incorporation by of Boeing 

Service Bulletin 767–54A0101, Revision 3, 

dated September 5, 2002. 

(3) On May 15, 2001 (66 FR 18523, April 

10, 2001), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Service Bulletin 767–54A0101, 

Revision 1, dated February 3, 2000. 

(4) 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 

September 13, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18785 Filed 9–21–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–66–AD; Amendment 

39–14289; AD 2005–19–24] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 727 Series Airplanes 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Boeing Model 727 

series airplanes, that currently requires 

repetitive pre-modification inspections 

to detect cracks in the forward support 

fitting of the number 1 and number 3 

engines; and repair, if necessary. That 

AD also provides for an optional high 

frequency eddy current inspection, and, 

if possible, modification of the fastener 

holes; and various follow-on actions; 

which would terminate the repetitive 

pre-modification inspections. This 

amendment expands the area to be 

inspected; requires accomplishment of 

the previously optional (and 

subsequently revised) modification, 

which terminates certain repetitive 

inspections; and adds repetitive postmodification inspections to detect 

cracking of the fastener holes, and 

corrective actions if necessary. The 

actions specified by this AD are 

intended to prevent fatigue cracking of 

the forward support fitting of the 

number 1 and number 3 engines, which 

could result in failure of the support 

fitting and consequent separation of the 

engine from the airplane. This action is