Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 51903 

MAXIMUM TURKEY INSPECTION RATES

Inspection system Line configuration 

Number of 

inspectors 

Birds/minute 

J-Type Bar-Type 

(<16#) 

light 

(>16#) 1

heavy 

(<16#) 

light 

(>16#) 1

heavy 

NTI–1 ......................................................................... 12–1 1 32 30 25 21 

NTI–2 ......................................................................... 2 24–2 2 51 41 45 35 

NTI–1 Modified ........................................................... 12–1 1 — — 32 30 

NTI–2 Modified ........................................................... 2 24–2 2 — — 51 41 

1This weight refers to the bird at the point of post-mortem inspection without blood or feet. 

2The turkeys are suspended on the slaughter line at 12-inch intervals with two inspectors each looking at alternating birds at 24-inch intervals. 

Done in Washington, DC, on August 29, 

2008. 

Alfred V. Almanza, 

Administrator. 

[FR Doc. E8–20551 Filed 9–5–08; 8:45 am] 

BILLING CODE 3410–DM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0356; Directorate 

Identifier 2008–NM–042–AD; Amendment 

39–15661; AD 2008–18–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–400 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 Bombardier 

Model DHC–8–400 series airplanes. 

That AD currently requires inspecting 

all barrel nuts to determine if the barrel 

nuts have a certain marking, inspecting 

affected bolts to determine if the bolts 

are pre-loaded correctly, and replacing 

all hardware if the pre-load is incorrect. 

For airplanes on which the pre-load is 

correct, the existing AD requires doing 

repetitive visual inspections for 

cracking of the barrel nuts and cradles 

and replacing all hardware for all 

cracked barrel nuts. The existing AD 

also requires replacing all hardware for 

certain affected barrel nuts that do not 

have cracking, which would end the 

repetitive inspections for those 

airplanes. The existing AD also provides 

an optional replacement for all affected 

barrel nuts. This new AD requires 

replacing all affected barrel nuts and 

applying a certain compound to the 

affected barrel nuts and bolts. This AD 

results from reports of cracking in the 

barrel nuts at the four primary front spar 

wing-to-fuselage attachment joints. We 

are issuing this AD to detect and correct 

cracking of the barrel nuts at the wing 

front spar wing-to-fuselage joints, which 

could result in reduced structural 

integrity of the wing-to-fuselage 

attachments and consequent 

detachment of the wing. 

DATES: This AD becomes effective 

October 14, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 14, 2008. 

On February 13, 2008 (73 FR 8187, 

February 13, 2008), the Director of the 

Federal Register approved the 

incorporation by reference of 

Bombardier Alert Service Bulletin A84–

57–19, Revision A, dated February 6, 

2008. 

ADDRESSES: For service information 

identified in this AD, contact 

Bombardier, Inc., Bombardier Regional 

Aircraft Division, 123 Garratt Boulevard, 

Downsview, Ontario M3K 1Y5, Canada. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Pong Lee, Aerospace Engineer, Airframe 

and Propulsion Branch, ANE–171, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7324; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that supersedes AD 2008–04–02, 

amendment 39–15374 (73 FR 8187, 

February 13, 2008). The existing AD 

applies to certain Bombardier Model 

DHC–8–400 series airplanes. That 

supplemental NPRM was published in 

the Federal Register on June 26, 2008 

(73 FR 36285). That supplemental 

NPRM proposed to continue to require 

inspecting all barrel nuts to determine if 

the barrel nuts have a certain marking, 

inspecting affected bolts to determine if 

the bolts are pre-loaded correctly, and 

replacing all hardware if the pre-load is 

incorrect. For airplanes on which the 

pre-load is correct, that supplemental 

NPRM also proposed to continue to 

require doing repetitive visual 

inspections for cracking of the barrel 

nuts and cradles and replacing all 

hardware for all cracked barrel nuts. 

That supplemental NPRM also proposed 

to continue to require replacing all 

hardware for certain affected barrel nuts 

that do not have cracking, which would 

end the repetitive inspections for those 

airplanes. In addition, that 

supplemental NPRM also proposed to 

continue to provide an optional 

replacement for all affected barrel nuts. 

Finally, that supplemental NPRM also 

proposed to require replacing all 

affected barrel nuts and applying a 

certain compound to the affected barrel 

nuts and bolts. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 


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51904 Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

This AD affects about 48 airplanes of 

U.S. registry. 

The actions that are required by AD 

2008–04–02 and retained in this AD 

take about 3 work hours per airplane, at 

an average labor rate of $80 per work 

hour. Based on these figures, the 

estimated cost of the currently required 

actions is $11,520, or $240 per airplane, 

per inspection cycle. 

Replacement of the hardware of a 

barrel nut, if required, takes about 12 

work hours per airplane, at an average 

labor rate of $80 per work hour. 

Required parts cost about $800 per 

barrel nut. Based on these figures, we 

estimate the cost of a replacement to be 

$1,760 per barrel nut. 

Application of the compound, if 

required, takes about 4 work hours per 

airplane, at an average labor rate of $80 

per work hour. Based on these figures, 

we estimate the cost of a replacement to 

be $320 per application. 

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 39–15374 (73 

FR 8187, February 13, 2008) and by 

adding the following new airworthiness 

directive (AD): 

2008–18–04 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–15661. 

Docket No. FAA–2008–0356; Directorate 

Identifier 2008–NM–042–AD. 

Effective Date 

(a) This AD becomes effective October 14, 

2008. 

Affected ADs 

(b) This AD supersedes AD 2008–04–02. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400, DHC–8–401, and DHC–8–402 

airplanes, certificated in any category; serial 

numbers 4001 and 4003 through 4176 

inclusive. 

Unsafe Condition 

(d) This AD results from reports of cracking 

in the barrel nuts at the four primary front 

spar wing-to-fuselage attachment joints. We 

are issuing this AD to detect and correct 

cracking of the barrel nuts at the wing front 

spar wing-to-fuselage joints, which could 

result in reduced structural integrity of the 

wing-to-fuselage attachments and consequent 

detachment of the wing. 

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 2008– 

04–02 With New Service Information 

Inspections and Corrective Actions 

(f) Within 50 flight hours after February 13, 

2008 (the effective date of AD 2008–04–02), 

inspect all barrel nuts, part number DSC228–

16, to determine if the barrel nuts are 

identified with a marking of LH7940T SPS 

01. Inspect in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A84–57–19, Revision 

A, dated February 6, 2008; or Revision B, 

dated March 6, 2008. As of the effective date 

of this AD, Bombardier Alert Service Bulletin 

A84–57–19, Revision B, dated March 6, 2008, 

must be used. 

(1) If no barrel nuts are identified with a 

marking of LH7940T SPS 01, no further 

actions are required by this paragraph. 

(2) If any barrel nut is found that is 

identified with a marking of LH7940T SPS 

01, before further flight, inspect the inboard 

and outboard bolts to determine if the bolts 

are pre-loaded correctly. Inspect in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A84–57–19, Revision A, dated 

February 6, 2008; or Revision B, dated March 

6, 2008. As of the effective date of this AD, 

Bombardier Alert Service Bulletin A84–57–

19, Revision B, dated March 6, 2008, must be 

used. 

(i) If the pre-load is incorrect (i.e., the ring 

can be rotated), before further flight, replace 

all hardware at that location in accordance 

with the Accomplishment Instructions of the 

alert service bulletin. 

(ii) If the pre-load is correct, before further 

flight, do a visual inspection for cracking of 

the barrel nuts and cradles in accordance 

with the Accomplishment Instructions of the 

alert service bulletin. 

(A) If no cracking of the barrel nut and 

cradle is found, do the applicable action 

required by paragraph (g) of this AD. 

(B) If no cracking of the barrel nut is found 

and only cracking of the cradle is found, no 

action is required by this paragraph provided 

that the applicable corrective action specified 

in paragraph (g) of this AD is done. 

(C) If any cracking of the barrel nut is 

found, before next flight, replace all 

hardware only at that location in accordance 

with the Accomplishment Instructions of the 

alert service bulletin. 

(g) For any barrel nuts on which no 

cracking of the barrel nut was found during 

the inspection required by paragraph (f)(2)(ii) 

of this AD, do the applicable corrective 

action specified in paragraph (g)(1), (g)(2), 

(g)(3), (g)(4), or (g)(5) of this AD at the 

compliance time specified in the applicable 

paragraph. 

(1) If four barrel nuts having no cracking 

are found, do the actions specified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD. 

(i) Within 50 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD. Thereafter, repeat 

the inspection at intervals not to exceed 50 


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Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 51905 

flight hours until the replacement specified 

in paragraph (g)(1)(ii) of this AD is done. 

(ii) Within 100 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, replace all hardware at the left-hand 

outboard location and the right-hand 

outboard location in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A84–57–19, Revision 

A, dated February 6, 2008; or Revision B, 

dated March 6, 2008. As of the effective date 

of this AD, Bombardier Alert Service Bulletin 

A84–57–19, Revision B, dated March 6, 2008, 

must be used. Replacing the barrel nuts on 

the outboard locations terminates the 

requirement to do the repetitive inspections 

specified in paragraph (g)(1)(i) of this AD. 

(iii) Within 100 flight hours after doing the 

replacement required by paragraph (g)(1)(ii) 

of this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD for the remaining 

barrel nuts identified with a marking of 

LH7940T SPS 01. Thereafter, repeat the 

inspection at intervals not to exceed 100 

flight hours until the replacement of all 

hardware at those locations is done. Do the 

inspection and replacement in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A84–57–

19, Revision A, dated February 6, 2008; or 

Revision B, dated March 6, 2008. As of the 

effective date of this AD, Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008, must be used. 

(2) If three barrel nuts having no cracking 

are found, do the actions specified in 

paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of 

this AD. 

(i) Within 50 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD. Thereafter, repeat 

the inspection at intervals not to exceed 50 

flight hours until the replacement specified 

in paragraph (g)(2)(ii) of this AD is done. 

(ii) Within 100 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, replace all hardware for one affected 

barrel nut at the outboard location, on the 

side with two affected barrel nuts, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A84–57–19, Revision A, dated 

February 6, 2008; or Revision B, dated March 

6, 2008. As of the effective date of this AD, 

Bombardier Alert Service Bulletin A84–57–

19, Revision B, dated March 6, 2008, must be 

used. Replacing the barrel nut on the 

outboard location terminates the requirement 

to do the repetitive inspections specified in 

paragraph (g)(2)(i) of this AD. 

(iii) Within 100 flight hours after doing the 

replacement required by paragraph (g)(2)(ii) 

of this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD for the remaining 

barrel nuts identified with a marking of 

LH7940T SPS 01. Thereafter, repeat the 

inspection at intervals not to exceed 100 

flight hours until the replacement of all 

hardware at those locations is done. Do the 

inspection and replacement in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A84–57–

19, Revision A, dated February 6, 2008; or 

Revision B, dated March 6, 2008. As of the 

effective date of this AD, Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008, must be used. 

(3) If two barrel nuts having no cracking 

are found and both nuts are on the same side, 

do the actions specified in paragraphs 

(g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD. 

(i) Within 100 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD. Thereafter, repeat 

the inspection at intervals not to exceed 100 

flight hours until the replacement specified 

in paragraph (g)(3)(ii) of this AD is done. 

(ii) Within 500 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, replace all hardware for one affected 

barrel nut at the outboard location that has 

two affected barrel nuts in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A84–57–

19, Revision A, dated February 6, 2008; or 

Revision B, dated March 6, 2008. As of the 

effective date of this AD, Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008, must be used. 

Replacing the barrel nut on the outboard 

location terminates the requirement to do the 

repetitive inspections specified in paragraph 

(g)(3)(i) of this AD. 

(iii) Within 100 flight hours after doing the 

replacement required by paragraph (g)(3)(ii) 

of this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD for the remaining 

barrel nut identified with a marking of 

LH7940T SPS 01. Thereafter, repeat the 

inspection at intervals not to exceed 100 

flight hours until the replacement of all 

hardware at that location is done. Do the 

inspection and replacement in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A84–57–

19, Revision A, dated February 6, 2008; or 

Revision B, dated March 6, 2008. As of the 

effective date of this AD, Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008, must be used. 

(4) If two barrel nuts having no cracking 

are found and are on opposite sides, within 

100 flight hours after doing the inspection 

required by paragraph (f)(2)(ii) of this AD, 

repeat the inspection specified in paragraph 

(f)(2) of this AD. Thereafter, repeat the 

inspection at intervals not to exceed 100 

flight hours until the replacement of all 

hardware at those locations is done. Do the 

inspection and replacement in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A84–57–

19, Revision A, dated February 6, 2008; or 

Revision B, dated March 6, 2008. As of the 

effective date of this AD, Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008, must be used. 

(5) If one barrel nut having no cracking is 

found, within 100 flight hours after doing the 

inspection required by paragraph (f)(2)(ii) of 

this AD, repeat the inspection specified in 

paragraph (f)(2) of this AD. Thereafter, repeat 

the inspection at intervals not to exceed 100 

flight hours until the replacement of all 

hardware at that location is done. Do the 

inspection and replacement in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A84–57–

19, Revision A, dated February 6, 2008; or 

Revision B, dated March 6, 2008. As of the 

effective date of this AD, Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008, must be used. 

Actions Accomplished According to 

Previous Issue of Alert Service Bulletin 

(h) Actions accomplished before February 

13, 2008, in accordance with Bombardier 

Alert Service Bulletin A84–57–19, dated 

February 1, 2008, are acceptable for 

compliance with the corresponding actions 

specified in this AD. 

Actions Accomplished According to 

Bombardier Alert Service Bulletin A84–57–

18 

(i) For airplanes on which the actions 

specified in Bombardier Alert Service 

Bulletin A84–57–18, dated January 16, 2008, 

were accomplished before February 13, 2008, 

and on which no barrel nuts were found that 

were identified with a marking of LH7940T 

SPS 01: No further action is required by this 

AD. 

Parts Installation 

(j) As of February 13, 2008, no person may 

install a barrel nut, part number DSC228–16, 

identified with a marking of LH7940T SPS 

01, on any airplane. 

New Requirement of This AD 

Replacement of All Affected Barrel Nuts 

(k) For airplanes on which barrel nuts are 

inspected in accordance with paragraph 

(g)(1)(iii), (g)(2)(iii), (g)(3)(iii), (g)(4), or (g)(5) 

of this AD: Within 3,000 flight hours after the 

effective date of this AD, replace all hardware 

for all remaining barrel nuts, part number 

DSC228–16, identified with a marking of 

LH7940T SPS 01. Do the replacement in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A84–57–19, Revision B, dated 

March 6, 2008. Replacement of all hardware 

for all affected barrel nuts constitutes 

terminating action for the repetitive 

inspections of this AD. 

(l) For airplanes on which hardware for the 

barrel nut was replaced in accordance with 

Bombardier Alert Service Bulletin A84–57–

19, dated February 1, 2008; or Revision A, 

dated February 6, 2008: Within 3,000 flight 

hours after the effective date of this AD, 

apply F13, Type 2 corrosion inhibiting 

compound to the affected bolts and barrel 

nuts in accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A84–57–19, Revision B, dated 

March 6, 2008; except if it can be 

conclusively determined from a review of 

airplane maintenance records that F13, Type 

2 corrosion inhibiting compound was 

applied to the affected bolts and barrel nuts, 

then no further action is required by this 

paragraph. 

Special Flight Permit 

(m) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), may be issued to operate the 

airplane to a location where the requirements 

of this AD can be accomplished, but 

concurrence by the Manager, New York 

Aircraft Certification Office (ACO), FAA, is 


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51906 Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 

required prior to issuance of the special flight 

permit. Before using any approved special 

flight permits, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. Special flight permits 

may be permitted provided that the 

conditions specified in paragraphs (m)(1), 

(m)(2), (m)(3), (m)(4), and (m)(5) of this AD 

are met. 

(1) Both the right-hand side and left-hand 

side of the airplane must have at least one 

barrel nut that is not within the suspect batch 

(i.e., barrel nut is not identified with a 

marking of LH7940T SPS 01). The barrel nuts 

that are not within the suspect batch must be 

in good working condition (i.e., no cracking 

of the barrel nut). 

(2) No passengers and no cargo are 

onboard. 

(3) Airplane must operate in fair weather 

conditions with a low risk of turbulence. 

(4) Airplane must operate with reduced 

airspeed. For further information, contact 

Bombardier, Q Series 24 Hour Service 

Customer Response Center, at: Telephone 1–

416–375–4000; fax 1–416–375–4539; E-mail: 

thd.qseries@aero.bombardier.com. 

(5) All of the conditions specified in 

paragraphs (m)(1), (m)(2), (m)(3), and (m)(4) 

of this AD are on a case-by-case basis. 

Contact your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO, for assistance. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, New York ACO, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Pong Lee, Aerospace Engineer, Airframe and 

Propulsion Branch, ANE–171, FAA, New 

York ACO, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone (516) 

228–7324; fax (516) 794–5531. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

Related Information 

(o) Canadian airworthiness directive CF–

2008–11R1, dated May 9, 2008, also 

addresses the subject of the AD. 

Material Incorporated by Reference 

(p) You must use Bombardier Alert Service 

Bulletin A84–57–19, Revision A, dated 

February 6, 2008; or Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008; as applicable; to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Bombardier Alert Service Bulletin A84–57–

19, Revision B, dated March 6, 2008, in 

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

part 51. 

(2) On February 13, 2008 (73 FR 8187, 

February 13, 2008), the Director of the 

Federal Register approved the incorporation 

by reference of Bombardier Alert Service 

Bulletin A84–57–19, Revision A, dated 

February 6, 2008. 

(3) Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 1Y5, 

Canada, for a copy of this service 

information. You may review copies at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

18, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19718 Filed 9–5–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0672; Directorate 

Identifier 2008–NM–032–AD; Amendment 

39–15660; AD 2008–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, and A340–300 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During manufacturing of A330/A340 

aircraft framework, cracks have been found 

on Frame (FR) 12, left (LH) and right (RH) 

sides. It has been confirmed that a defect of 

the FR12 forming tool press is the root cause 

of the cracks. 

If undetected such damage could affect, 

after propagation, the structural integrity of 

the aircraft. 

* * * * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 24, 2008 (73 FR 35595). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During manufacturing of A330/A340 

aircraft framework, cracks have been found 

on Frame (FR) 12, left (LH) and right (RH) 

sides. It has been confirmed that a defect of 

the FR12 forming tool press is the root cause 

of the cracks. 

If undetected such damage could affect, 

after propagation, the structural integrity of 

the aircraft. 

In order to permit an early detection and 

repair of cracks on FR12, LH and RH sides, 

this Airworthiness Directive (AD) mandates a 

one time High Frequency Eddy Current 

(HFEC) inspection of FR12. 

Corrective actions include, for certain 

findings, contacting Airbus for repair 

instructions and doing the repair; 

repairing cracking (i.e., installing a new 

splice); and applying new protective 

coatings and corrosion inhibitors. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 


pwalker on PROD1PC71 with RULES