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 

Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55525 

intended to address the identified 

unsafe condition. 

DATES: Effective October 27, 2005. 

The incorporation by reference of 

Boeing Service Bulletin 727–54A0010, 

Revision 6, including Appendix A, 

dated August 23, 2001, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of October 27, 

2005. 

The incorporation by reference of 

Boeing Service Bulletin 727–54A0010, 

Revision 4, dated January 30, 1997, as 

listed in the regulations, was approved 

previously by the Director of the Federal 

Register as of March 18, 1997 (62 FR 

9359, March 3, 1997). 

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington. 

FOR FURTHER INFORMATION CONTACT: 

Daniel F. Kutz, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6456; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 97–05–08, 

amendment 39–9952 (62 FR 9359, 

March 3, 1997), which is applicable to 

all Boeing Model 727 series airplanes, 

was published in the Federal Register 

on May 1, 2003 (68 FR 23231). The 

action proposed to continue to require 

repetitive pre-modification inspections 

to detect cracks in the forward support 

fitting of the number 1 and number 3 

engines, and repair if necessary. The 

action also proposed to expand the area 

to be inspected; require accomplishment 

of the previously optional (and 

subsequently revised) modification, 

which would terminate certain 

repetitive inspections; and add 

repetitive post-modification inspections 

to detect cracking of the fastener holes, 

and corrective actions if necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Requests To Revise the Applicability 

One commenter requests that the 

applicability of the proposed AD be 

revised to apply only to Boeing Model 

727 airplanes equipped with fittings 

having part number (P/N) 65–18722–xx. 

The commenter states that its Model 

727–100 fleet does not include any 

airplanes equipped with fittings having 

that P/N. Because it changed the 

affected fittings during a re-engine 

modification in accordance with 

Supplemental Type Certificate (STC) 

SA8472SW, it was granted an alternate 

method of compliance (AMOC) for AD 

97–05–08. The commenter asserts that 

revising the proposed applicability will 

prevent operators that do not have the 

affected fittings installed from having to 

request an AMOC for the requirements 

of the proposed AD. 

Another commenter requests that a 

statement be added to the proposed AD 

to exempt airplanes modified in 

accordance with STC SA4363NM. The 

commenter asserts that inclusion of this 

statement will make it perfectly clear to 

operators whether or not they are in 

compliance with the AD. 

We acknowledge the commenters’

concern and, as we state in paragraph 

(t)(2) of this AD, AMOCs previously 

approved according to AD 97–05–08 are 

acceptable for compliance with the 

corresponding requirements of this AD. 

These AMOCs address the commenter’s 

concern. We find that no further 

clarifications are necessary and have 

made no change to the final rule in this 

regard. 

Request To Add Language Specific to 

Airplanes With ‘‘Hush Kit’’ STCs 

Installed 

A third commenter requests that 

specific language be included in the 

final rule stating that airplanes modified 

in accordance with STCs SA3993NM, 

SA4833NM, SA5839NM, and 

ST00350AT may be inspected and 

modified in accordance with Boeing 

Service Bulletin 727–54A0010, Revision 

6, without change. (Boeing Service 

Bulletin 727–54A0010, Revision 6, 

dated August 23, 2001, was referenced 

in the proposed AD as the appropriate 

source of service information for 

accomplishing the new actions). These 

STCs install noise suppression 

modification equipment (hush kits) on 

Model 727 airplanes. The commenter 

states that including this information in 

the AD, in lieu of making operators 

request AMOCs, will avoid confusion 

among operators with airplanes 

equipped with these STCs. The 

commenter submitted substantiating 

data to support its request. 

We do not agree. The static strength 

data analysis of the affected structure 

submitted was not sufficient to show 

that the commenter’s request would 

result in an acceptable level of safety. 

Damage tolerance assessment is needed 

to determine if the inspections and 

modifications described in Boeing 

Service Bulletin 727–54A0010, Revision 

6, are appropriate for airplanes modified 

in accordance with these STCs. In this 

case, the ability to inspect the affected 

area and changes in fatigue stress levels 

need to be addressed. Additionally, the 

inspections and modifications specified 

in the service bulletin specifically 

address only affected original 

equipment manufacturer configurations. 

However, as we explained previously, 

we will consider requests for AMOCs 

submitted with sufficient technical 

justification to support the request. We 

have made no change to the final rule 

regarding this issue. 

Request To Change the Method of 

Inspection 

Another commenter, the 

manufacturer, requests that we revise 

paragraphs (d)(1) and (d)(3) of the 

proposed AD to revise the method of 

inspection. Specifically, the commenter 

recommends revising ‘‘* * * If any 

corrosion is found, before further flight, 

remove the corrosion in accordance 

with Figure 5 of the service bulletin, 

and perform a general visual inspection 

to detect cracking * * *’’ to read 

‘‘* * * If any corrosion is found, before 

further flight, remove the corrosion in 

accordance with Figure 5 of the service 

bulletin, and perform a HFEC inspection 

to detect cracking * * *.’’ The 

commenter asserts that the high 

frequency eddy current (HFEC) 

inspection is a better method than a 

surveillance inspection and will provide 

an adequate level of safety by enabling 

operators to find small cracks. 

We partially agree with the 

commenter. We find that an HFEC 

inspection should be accomplished after 

removal of corrosion. However, we do 

not agree that it is necessary to revise 

paragraphs (d)(1) and (d)(3) of this final 

rule as requested. Paragraphs (d)(1) and 

(d)(3) require any corrosion found to be 

removed in accordance with Figure 5 of 

Boeing Service Bulletin 727–54A0010, 

Revision 6, dated August 23, 2001. Step 

5 of Figure 5 of the service bulletin 

includes procedures for doing an HFEC 

inspection for cracks and repairing any 

cracks found once the corrosion has 

been identified and removed from the 

affected area. The general visual 

inspection required by paragraphs (d)(1) 

and (d)(3) follows the instructions given 

in Figure 1, Step 2, of the service 

bulletin. We find that no change to the 

final rule is necessary regarding this 

issue. 

55526 Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 

Request To Refer Specifically to PostModification Inspections 

The same commenter also requests 

that paragraph (m) of the proposed AD 

be revised to refer to the postmodification inspections in Revision 5 

of Boeing Alert Service Bulletin 727–

54A0010, dated February 15, 2001. 

Specifically, the commenter 

recommends revising ‘‘* * * 

Inspections done before the effective 

date of this AD in accordance with 

Boeing Alert Service Bulletin 727–

54A0010, Revision 5, dated February 15, 

2001, are acceptable for compliance 

with the corresponding inspection 

requirements of this paragraph * * *.’’

to ‘‘* * * Inspections done before the 

effective date of this AD in accordance 

with Part III of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 727–54A0010, Revision 5, 

dated February 15, 2001, are acceptable 

for compliance with the corresponding 

inspection requirements of this 

paragraph * * *.’’ The commenter 

believes that, for airplanes that have 

accomplished the modification, only the 

repeat post-modification inspection 

requirements of Revision 5 of the 

service bulletin provide an equivalent 

level of safety for the fleet. 

We agree with the request for the 

reason provided by the commenter. It 

was our intent to refer specifically to 

Part III of the Accomplishment 

Instructions of Revision 5 of the service 

bulletin in paragraph (m). Therefore, we 

have revised paragraph (m) of this final 

rule to specifically refer to Part III of the 

Accomplishment Instructions of 

Revision 5 of the service bulletin for 

accomplishment of post-modification 

inspections done before the effective 

date of the AD. 

Explanation of Additional Changes to 

the Proposed AD 

Boeing has received a Delegation 

Option Authorization (DOA). We have 

revised this final rule to delegate the 

authority to approve an alternative 

method of compliance for any repair 

required by this AD to the Authorized 

Representative for the Boeing DOA 

Organization rather than the Designated 

Engineering Representative (DER). 

Accordingly, we have added paragraph 

(t)(3) to this final rule and revised the 

wording of paragraphs (h)(1) and (i) of 

this AD. We have also revised the 

wording of paragraph (t)(1) of this final 

rule (specified as paragraph (s)(1) in the 

proposed AD) for reasons discussed 

under ‘‘Changes to 14 CFR part 39/Effect 

on the AD.’’

Because the language in Note 6 of the 

proposed AD is regulatory in nature, 

that note has been redesignated as 

paragraph (r) of this final rule. We have 

re-identified subsequent notes and 

paragraphs accordingly. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Changes to 14 CFR Part 39/Effect on the 

AD 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

FAA’s airworthiness directives system. 

The regulation now includes material 

that relates to altered products, special 

flight permits, and AMOCs. Because we 

have now included this material in part 

39, only the office authorized to approve 

AMOCs is identified in each individual 

AD. However, for clarity and 

consistency in this final rule, we have 

retained the language of the NPRM 

regarding that material, except for the 

revisions to certain language discussed 

previously. 

Change to Labor Rate Estimate and 

Airplane Fleet Data 

We have reviewed the figures we have 

used over the past several years to 

calculate AD costs to operators. To 

account for various inflationary costs in 

the airline industry, we find it necessary 

to increase the labor rate used in these 

calculations from $60 per work hour to 

$65 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

We have also revised the cost impact 

information to more accurately describe 

the number of airplanes of the affected 

design in the current worldwide and 

U.S. fleets. 

Cost Impact 

There are approximately 1,009 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

587 airplanes of U.S. registry will be 

affected by this AD. 

We provide the following cost 

estimates for this AD: 

Action Work 

hours 

Average 

labor rate 

per hour 

Cost of 

parts 

Cost per 

airplane Cost for the U.S. fleet 

AD 97–05–08 inspections, per inspection 

cycle.

2 $65 $0 $130 $76,310, per inspection cycle. 

Inspections before structural rework, per 

inspection cycle.

14 65 0 910 534,170, per inspection cycle. 

Structural rework ....................................... 7 65 7,875 8,330 4,889,710. 

Inspections after structural rework, per inspection cycle.12 65 0 780 457,860, per inspection cycle. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55527 

‘‘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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by 

removing amendment 39–9952 (62 FR 

9359, March 3, 1997), and by adding a 

new airworthiness directive (AD), 

amendment 39–14289, to read as 

follows: 

2005–19–24 Boeing: Amendment 39–14289. 

Docket 2002–NM–66–AD. Supersedes 

AD 97–05–08, Amendment 39–9952. 

Applicability: All Model 727 series 

airplanes, certificated in any category. 

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (t)(1) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it. 

Compliance: Required as indicated, unless 

accomplished previously. 

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, accomplish the 

following: 

Restatement of Requirements of AD 97–05–

08 

Inspections 

(a) Within 100 days or 600 flight cycles 

after March 18, 1997 (the effective date of AD 

97–05–08, amendment 39–9952), whichever 

occurs first, accomplish paragraphs (a)(1), 

(a)(2), and (a)(3) of this AD, in accordance 

with Boeing Service Bulletin 727–54A0010, 

Revision 4, dated January 30, 1997. 

(1) Perform a visual inspection to detect 

cracks of the upper and lower flanges, and 

the vertical web of the forward support fitting 

of the number 1 and number 3 engines, in 

accordance with Part 1—Pre-Modification 

Inspections of the Accomplishment 

Instructions of the service bulletin. 

(2) Perform a high frequency eddy current 

(HFEC) inspection to detect cracks of the 

forward flange of the support fitting adjacent 

to the collars of two fasteners of the number 

1 and number 3 engines, in accordance with 

Part 1—Pre-Modification Inspections of the 

Accomplishment Instructions of the service 

bulletin. 

(3) Perform a detailed inspection to detect 

cracks of the upper and lower flanges 

adjacent to six fasteners of the fitting of the 

number 1 and number 3 engines, in 

accordance with Part 1—Pre-Modification 

Inspections of the Accomplishment 

Instructions of the service bulletin. 

Note 2: 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.’’

(b) If no crack is detected during the 

inspections required by paragraph (a) of this 

AD, repeat those inspections thereafter at 

intervals not to exceed 100 days or 600 flight 

cycles, whichever occurs first, until the 

initial inspections required by paragraph (d) 

of this AD have been accomplished. 

(c) If any crack is detected during any 

inspection required by paragraph (a) of this 

AD, prior to further flight, repair the forward 

support fitting in accordance with a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA. 

New Requirements of This AD 

Note 3: Where there are differences 

between the service bulletin and this AD, this 

AD prevails. 

Inspections: All Airplanes 

(d) For all airplanes: Within 600 flight 

cycles or 100 days after the effective date of 

this AD, whichever occurs first, inspect the 

forward support fitting of the number 1 and 

number 3 engines, as specified in paragraphs 

(d)(1), (d)(2), (d)(3), (d)(4), and (d)(5) of this 

AD, in accordance with Part I of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–54A0010, Revision 6, 

dated August 23, 2001. Accomplishment of 

these initial inspections terminates the 

inspection requirements of paragraphs (a) 

and (b) of this AD. 

(1) Perform a general visual inspection to 

detect corrosion and cracking of the fittings 

in areas inboard of the side of the body, in 

accordance with Figure 1 of the service 

bulletin. If any corrosion is found, before 

further flight, remove the corrosion by 

accomplishing all of the actions in and in 

accordance with Figure 5 of the service 

bulletin, and then perform a general visual 

inspection to detect cracking of the area, in 

accordance with the service bulletin. 

Note 4: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(2) Perform an HFEC inspection to detect 

cracking of the upper and lower horizontal 

flanges and post tangs of the fittings from 

inside the airplane, in accordance with 

Figure 1 of the service bulletin. 

(3) Perform a general visual inspection to 

detect cracking and corrosion of the fittings 

in areas outboard of the side of the body, in 

accordance with Figure 1 of the service 

bulletin. If any corrosion is found, before 

further flight, remove the corrosion by 

accomplishing all of the actions in and in 

accordance with Figure 5 of the service 

bulletin, and perform a general visual 

inspection to detect cracking of the area, in 

accordance with the service bulletin. 

(4) Perform a detailed inspection to detect 

cracking and corrosion of the web in areas 

outboard of the side of the body, in 

accordance with Figure 1 of the service 

bulletin. If any corrosion is found, before 

further flight, remove the corrosion in 

accordance with Figure 5 of the service 

bulletin, and perform thickness 

measurements and detailed and HFEC 

inspections of the vertical web inboard and 

outboard of the side of the body to detect 

corrosion and cracking, in accordance with 

Figure 2 of the service bulletin. If the web 

thickness is less than 0.130 inch, do 

paragraph (i) of this AD. 

(5) Perform detailed and HFEC inspections 

to detect cracking of the upper and lower 

horizontal flanges at the side of the body, in 

accordance with Figure 1 of the service 

bulletin. 

Additional Inspections: Group 2 Airplanes 

(e) For Group 2 airplanes, as identified in 

Boeing Service Bulletin 727–54A0010, 

Revision 6, dated August 23, 2001: Within 

600 flight cycles or 100 days after the 

effective date of this AD, whichever occurs 

first, inspect the forward support fitting of 

the number 1 and number 3 engines at the 

55528 Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 

firewall to detect cracking, as specified in 

paragraphs (e)(1), (e)(2), (e)(3), and (e)(4) of 

this AD, in accordance with Part I of the 

Accomplishment Instructions of the service 

bulletin. 

(1) Perform a detailed inspection to detect 

cracking of the aft side of the upper 

horizontal flange, in accordance with Figure 

1 of the service bulletin. 

(2) Perform a low frequency eddy current 

(LFEC) or an open hole HFEC inspection to 

detect cracking of the aft side of the upper 

horizontal flange, in accordance with Figure 

1 of the service bulletin. 

(3) Perform a detailed inspection to detect 

cracking of the aft side of the lower 

horizontal flange, in accordance with Figure 

1 of the service bulletin. 

(4) Perform an HFEC inspection to detect 

cracking of the aft side of the lower 

horizontal flange, in accordance with Figure 

1 of the service bulletin. 

No Cracking Found: Follow-on Inspections, 

All Airplanes 

(f) For all airplanes: If no cracking is found 

during any inspection required by paragraph 

(d) of this AD, repeat the applicable 

inspections within the applicable intervals 

specified in paragraph 1.E., Table 1, of 

Boeing Service Bulletin 727–54A0010, 

Revision 6, dated August 23, 2001, until the 

modification required by paragraph (j) of this 

AD has been done. 

No Cracking Found: Additional Follow-on 

Inspections, Group 2 Airplanes 

(g) For Group 2 airplanes only: If no 

cracking is found during the inspections 

required by paragraph (e) of this AD, repeat 

the inspections on the upper and lower 

outboard flange at the firewall within the 

applicable intervals specified in paragraph 

1.E., Table 1, of Boeing Service Bulletin 727–

54A0010, Revision 6, dated August 23, 2001. 

(1) Repeat the inspections of the upper 

outboard flange at the firewall until the 

modification required by paragraph (j) of this 

AD has been done. 

(2) Repeat the inspections of the lower 

outboard flange at the firewall indefinitely. 

There is no terminating action for the 

inspections of this area. 

Note 5: Boeing Service Bulletin 727–

54A0010, Revision 6, dated August 23, 2001, 

does not provide instructions for modifying 

the fastener holes of the lower outboard 

flange at the firewall. 

Cracking Found: Any Airplane 

(h) For any airplane: If any crack is found 

during any inspection required by paragraph 

(d), (e), (f), or (g) of this AD, before further 

flight, do the actions specified in either 

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

(1) Replace or repair the fitting in 

accordance with a method approved by the 

Manager, Seattle ACO; or according to data 

meeting the certification basis of the airplane 

approved by an Authorized Representative 

for the Boeing Delegation Option 

Authorization (DOA) 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; 

or 

(2) Do the modification specified in 

paragraph (j) of this AD. 

Web Thickness Less Than 0.130 Inch: Any 

Airplane 

(i) For any airplane: If the web thickness 

measured during accomplishment of 

paragraph (d)(4) of this AD is less than 0.130 

inch, before further flight, replace or repair 

the fitting in accordance with a method 

approved by the Manager, Seattle ACO; or 

according to data meeting the certification 

basis of the airplane approved by an 

Authorized Representative for the Boeing 

DOA 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. 

Modification 

(j) Except as required by paragraphs (h), (i), 

and (q) of this AD: Within 3,000 flight cycles 

or 24 months after the effective date of this 

AD, whichever occurs first, modify the 

fastener holes, in accordance with Part II of 

the Accomplishment Instructions of Boeing 

Service Bulletin 727–54A0010, Revision 6, 

dated August 23, 2001. Accomplishment of 

the modification terminates the repetitive 

inspections required by paragraphs (f) and 

(g)(1) of this AD. 

Modification in Accordance With Prior 

Service Bulletin Revision 

(k) For airplanes modified before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 727–54A0010, 

Revision 4, dated January 30, 1997: 

Paragraph (j) of this AD requires 

accomplishment of additional procedures in 

accordance with Revision 6 of the service 

bulletin. To the extent that certain 

modification procedures were performed in 

accordance with Revision 4, those actions do 

not need to be repeated when performing the 

modification required in paragraph (j) of this 

AD. 

(l) A modification done before the effective 

date of this AD in accordance with Boeing 

Alert Service Bulletin 727–54A0010, 

Revision 5, dated February 15, 2001, is 

acceptable for compliance with the 

requirements of paragraph (j) of this AD. 

Post-Modification Inspections 

(m) Inspect as specified in paragraphs 

(m)(1), (m)(2), and (n) of this AD, as 

applicable, to detect cracking and corrosion, 

in accordance with Part III of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–54A0010, Revision 6, 

dated August 23, 2001. Inspections done 

before the effective date of this AD in 

accordance with Part III of Boeing Alert 

Service Bulletin 727–54A0010, Revision 5, 

dated February 15, 2001, are acceptable for 

compliance with the corresponding 

inspection requirements of this paragraph. 

(1) For all airplanes: Do an open hole HFEC 

inspection of the fastener holes in the 

forward support fitting of the number 1 and 

number 3 engines, at the locations shown in 

Figure 4 of the service bulletin. 

(2) For Group 2 airplanes: Do an open hole 

HFEC inspection of the fastener holes in the 

forward support fitting of the number 1 and 

number 3 engines, at the locations shown in 

Figure 4 of the service bulletin. 

(n) Perform the inspections specified in 

paragraph (m) of this AD at the later of the 

times specified in paragraphs (n)(1) and 

(n)(2) of this AD. 

(1) Within 3,000 flight cycles or 24 months, 

whichever occurs first, after accomplishment 

of the modification required by paragraph (j) 

of this AD. 

(2) Within 600 flight cycles or 100 days, 

whichever occurs first, after the effective date 

of this AD. 

Follow-On/Corrective Actions 

(o) If no cracking is found during any 

inspection required by paragraph (m) of this 

AD: Repeat the inspections specified in 

paragraph (m) of this AD thereafter within 

the applicable intervals specified in 

paragraph 1.E., Table 1, of Boeing Service 

Bulletin 727–54A0010, Revision 6, dated 

August 23, 2001. Accomplishment of the 

modification specified in paragraph (j) of this 

AD does not terminate the requirement to 

repetitively perform the post-modification 

inspections specified in Part III of the service 

bulletin. 

(p) If any cracking is detected during any 

inspection required by paragraph (m) of this 

AD: Before further flight, repair in 

accordance with Boeing Service Bulletin 

727–54A0010, Revision 6, dated August 23, 

2001; except as required by paragraph (q) of 

this AD. 

Exception to Corrective Actions 

(q) Where Boeing Service Bulletin 727–

54A0010, Revision 6, dated August 23, 2001, 

specifies to contact Boeing for appropriate 

action: Before further flight, replace or repair 

the fitting in accordance with a method 

approved by the Manager, Seattle ACO; or 

according to data meeting the certification 

basis of the airplane approved by an 

Authorized Representative for the Boeing 

DOA 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. 

Reporting Not Required 

(r) Boeing Service Bulletin 727–54A0010, 

Revision 6, dated August 23, 2001, 

recommends that operators report inspection 

results to the manufacturer; however, this AD 

does not contain this requirement. 

Parts Installation 

(s) As of the effective date of this AD, no 

person may install a forward support fitting 

on any airplane, unless it has been inspected 

and modified, as applicable, in accordance 

with the requirements of this AD. 

Alternative Methods of Compliance 

(t)(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 previously approved according 

to AD 97–05–08 are acceptable for 

Federal Register / Vol. 70, No. 183 / Thursday, September 22, 2005 / Rules and Regulations 55529 

compliance with 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 

DOA 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. 

Note 6: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Seattle ACO. 

Special Flight Permits 

(u) Special flight permits may be issued 

according to sections 21.197 and 21.199 of 

the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(v) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

Boeing Service Bulletin 727–54A0010, 

Revision 4, dated January 30, 1997; and 

Boeing Service Bulletin 727–54A0010, 

Revision 6, including Appendix A, dated 

August 23, 2001; as applicable. 

(1) The incorporation by reference of 

Boeing Service Bulletin 727–54A0010, 

Revision 6, including Appendix A, dated 

August 23, 2001, is approved by the Director 

of the Federal Register in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) The incorporation by reference of 

Boeing Service Bulletin 727–54A0010, 

Revision 4, dated January 30, 1997, was 

approved previously by the Director of the 

Federal Register as of March 18, 1997 (62 FR 

9359, March 3, 1997). 

(3) Copies may be obtained from Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. Copies may 

be inspected 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 the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Effective Date 

(w) This amendment becomes effective on 

October 27, 2005. 

Issued in Renton, Washington, on 

September 8, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18783 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–2005–22486; Directorate 

Identifier 2004–NM–219–AD; Amendment 

39–14287; AD 2005–19–22] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–322, –341, and –342 Airplanes; 

and Airbus Model A340–200 and –300 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–322, –341, and 

–342 airplanes, and Model A340–200 

and –300 series airplanes. This AD 

requires modifying the left and right 

ram air outlets of the two air 

conditioning packs. The modification 

includes replacing the old air outlet 

assembly with a new air outlet 

assembly, and modifying the web. This 

AD results from a report of fatigue 

cracks that initiated in the duct 

structure of the ram air outlet, which is 

adjacent to the hydraulics compartment. 

We are issuing this AD to prevent 

fatigue cracks in the duct structure of 

the ram air outlet, which could lead to 

hot air damage and consequent loss of 

function of the hydraulics systems. 

DATES: Effective October 7, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 7, 2005. 

We must receive comments on this 

AD by November 21, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist for certain Airbus Model A330–

322, –341, and –342 airplanes, and 

Model A340–200 and –300 series 

airplanes. The DGAC advises that 

fatigue cracks have been found that 

initiated in the duct structure of the ram 

air outlet, which is adjacent to the 

hydraulics compartment. These fatigue 

cracks were found on airplanes that had 

been modified with an ‘‘adaptation 

solution’’ that was intended to prevent 

cracks and provide better thermal 

insulation. However, analyses showed 

that the adaptation solution did not 

prevent cracks that initiate after the 

12,000 flight-cycle threshold. Cracks in 

the duct structure could propagate, and 

certain rivet heads could shear from the 

inside. Either condition could cause the 

air outlet to rupture and lead to hot air 

being blown into the hydraulics bay. 

This condition, if not corrected, could 

result in hot air damage and consequent 

loss of function of the hydraulics 

systems. 

Relevant Service Information 

Airbus has issued the service 

bulletins listed in the following table. 

AIRBUS SERVICE BULLETINS

Airbus service bulletin— Revision Dated For model—

A330–53–3132 .......................................................... 02 April 26, 2004 .......... A330–322, –341, and –342 airplanes. 

A340–53–4139 .......................................................... 02 April 26, 2004 .......... A340–200 and –300 series airplanes