12120 Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations 

Washington 98055–4056; telephone 

(425) 917–6441; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: On 

January 31, 2005, the FAA issued AD 

2005–03–11, amendment 39–13967 (70 

FR 7174, February 11, 2005), for certain 

Boeing Model 767 series airplanes. The 

AD requires repetitive detailed and 

eddy current inspections of the aft 

pressure bulkhead for damage and 

cracking, and repair if necessary. The 

AD also requires one-time detailed and 

high frequency eddy current inspections 

of any ‘‘oil-can’’ located on the aft 

pressure bulkhead, and related 

corrective actions if necessary. 

As published, that final rule 

incorrectly specified the AD number in 

a single location in the AD as ‘‘2005–

NM–03–11’’ instead of ‘‘2005–03–11.’’

No other part of the regulatory 

information has been changed; 

therefore, the final rule is not 

republished in the Federal Register. 

The effective date of this AD remains 

March 18, 2005.

§ 39.13 [Corrected]

■ In the Federal Register of February 11, 

2005, on page 7175, in the first column, 

paragraph 2. of PART 39—

AIRWORTHINESS DIRECTIVES is 

corrected to read as follows:

* * * * *

2005–03–11 Boeing: Amendment 39–13967. 

Docket No. FAA–2004–19446; 

Directorate Identifier 2004–NM–130–AD.

* * * * *

Issued in Renton, Washington, on February 

28, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–4825 Filed 3–10–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19530; Directorate 

Identifier 2002–NM–274–AD; Amendment 

39–14008; AD 2005–05–19] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 727 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

727 airplanes. That AD currently 

requires repetitive detailed inspections 

to detect cracking, corrosion, and 

existing stop-drilled repairs of cracking 

in the upper chord of the rear spar of the 

wing; and repair if necessary. This new 

AD requires new repetitive inspections 

to detect cracks, corrosion, minor 

surface defects, and existing stop-drilled 

repairs of cracks in the upper and lower 

chords of the front and rear spars of the 

wing; and repair if necessary. This AD 

is prompted by our determination that 

further rulemaking action is necessary 

to require additional actions specified in 

the referenced service bulletin. We are 

issuing this AD to prevent structural 

failure of the wing and fuel leaks in the 

airplane due to stress corrosion cracking 

of the wing spar chords.

DATES: This AD becomes effective April 

15, 2005. 

On December 18, 2002 (67 FR 71808, 

December 3, 2002), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Alert Service Bulletin 727–57A0145, 

Revision 2, dated October 24, 2002.

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You can examine the 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 U.S. Department of Transportation, 

400 Seventh Street SW, room PL–401, 

Washington, DC. This docket number is 

FAA–2004–19530; the directorate 

identifier for this docket is 2002–NM–

274–AD.

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: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

Part 39) with an AD to supersede AD 

2002–24–05, amendment 39–12970 (67 

FR 71808, December 3, 2002). The 

existing AD applies to certain Boeing 

Model 727 airplanes. The proposed AD 

was published in the Federal Register

on November 5, 2004 (69 FR 64506), to 

require new repetitive inspections to 

detect cracks, corrosion, minor surface 

defects, and existing stop-drilled repairs 

of cracks in the upper and lower chords 

of the front and rear spars of the wing; 

and repair if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

submitted on the proposed AD. The 

commenter supports the proposed AD. 

Explanation of Change to Model 

Designation 

We have revised the subject heading 

of the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Changes to Delegation Authority 

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). 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We have determined that this change 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

There are about 1,426 airplanes of the 

affected design in the worldwide fleet. 

This AD will affect about 946 airplanes 

of U.S. registry. 

For Group 1 airplanes identified in 

the service bulletin, the actions (Part 1 

of the Accomplishment Instructions of 

the service bulletin) that are required by 

AD 2002–24–05 and retained in this AD 

take about 8 work hours per airplane, at 

an average labor rate of $65 per work 

hour. Based on these figures, the 

estimated cost of the currently required 

actions is $520 per airplane. 

The following table provides the 

estimated costs for U.S. operators to 

comply with the new actions required 

by this AD. The average labor rate is $65 

per work hour.

Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations 12121

ESTIMATED COSTS

For airplanes identified in the service bulletin as— Actions in— Work hours—

Per airplane 

cost, per

inspection 

cycle—

Group 1 ........................................................................... Part 2 of the Accomplishment Instructions of the 

service bulletin.

30 $1,950 

Group 1 ........................................................................... Part 3 of the Accomplishment Instructions of the 

service bulletin.

21 1,365 

Group 1 ........................................................................... Part 4 of the Accomplishment Instructions of the 

service bulletin.

68 4,420 

Group 1 ........................................................................... Part 8 of the Accomplishment Instructions of the 

service bulletin.

8 520 

Group 1 ........................................................................... Part 9 of the Accomplishment Instructions of the 

service bulletin.

30 1,950 

Group 2 ........................................................................... Part 5 of the Accomplishment Instructions of the 

service bulletin.

52 3,380 

Group 2 ........................................................................... Part 6 of the Accomplishment Instructions of the 

service bulletin.

110 7,150 

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. 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 FAA amends § 39.13 by 

removing amendment 39–12970 (67 FR 

71808, December 3, 2002), and by adding 

the following new airworthiness 

directive (AD):

2005–05–19 Boeing: Amendment 39–14008. 

Docket No. FAA–2004–19530; 

Directorate Identifier 2002–NM–274–AD. 

Effective Date 

(a) This AD becomes effective April 15, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2002–24–05, 

amendment 39–12970. 

Applicability 

(c) This AD applies to Boeing Model 727, 

727C, 727–100, –100C, –200, and –200F 

series airplanes, line numbers 1 through 1832 

inclusive; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by our 

determination that further rulemaking action 

is necessary to require additional actions 

specified in the referenced service bulletin. 

We are issuing this AD to prevent structural 

failure of the wing and fuel leaks in the 

airplane due to stress corrosion cracking of 

the wing spar chords. 

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. 

Service Bulletin References 

(f) The term ‘‘the service bulletin,’’ as used 

in this AD, means Boeing Alert Service 

Bulletin 727–57A0145, Revision 2, dated 

October 24, 2002. 

Inspection Requirements of AD 2002–24–05, 

Amendment 39–12970 

Inspection 

(g) For airplanes specified as ‘‘Group 1’’

airplanes in the service bulletin: Within 20 

years after the date of manufacture or within 

90 days after December 18, 2002 (the 

effective date of AD 2002–24–05, amendment 

39–12970), whichever occurs later, perform 

an external detailed inspection for cracking, 

corrosion, and existing stop-drilled repairs of 

cracking in the upper chord on the rear spar 

from Wing Butt Line (WBL) 70.5 through 

WBL 249.3, per the service bulletin, 

paragraph 3.B, ‘‘Work Instructions,’’ Part 1. 

Thereafter, repeat the inspection at intervals 

not to exceed 2 years.

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 mirrors, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

12122 Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations 

New Actions Required by This AD 

Inspections Specified in Parts 2 Through 6, 

and 8 and 9 of the Service Bulletin 

(h) Accomplish the applicable 

inspection(s) specified in paragraphs (h)(1) 

through (h)(7) of this AD at the later of the 

applicable times specified in the 

‘‘Threshold’’ and ‘‘Grace Period’’ columns in 

Table 1 of this AD, and repeat the 

inspection(s) at the time specified in the 

‘‘Repetitive Interval’’ column of Table 1 of 

this AD. Accomplishment of the inspection 

required by paragraph (h)(1) of this AD 

terminates the repetitive inspection 

requirements of paragraph (g) of this AD.

TABLE 1.—COMPLIANCE TIMES FOR INSPECTIONS SPECIFIED IN PARTS 2 THROUGH 6, AND 8 AND 9 OF SERVICE BULLETIN

For airplanes identified in 

the service bulletin as— Threshold— Grace period— Repetitive interval— Do—

(1) Group 1 ........................ Before 20 years since the 

date of issuance of the 

original Airworthiness 

Certificate or the date of 

issuance of the original 

Export Certificate of Airworthiness.

Within 1 year after the effective date of this AD.None .................................. A high frequency eddy current (HFEC) inspection 

and detailed inspection 

of the upper chord the 

rear spar from WBL 70.5 

to the wing tip for 

cracks, corrosion, minor 

surface defects, and existing stop-drilled repairs 

of cracking, in accordance with paragraph 

3.B., Work Instructions, 

Part 2, of the Accomplishment Instructions of 

the service bulletin. 

(2) Group 1 ........................ Before 20 years since the 

date of issuance of the 

original Airworthiness 

Certificate or the date of 

issuance of the Original 

Export Certificate of Airworthiness.

Within 2 years after the effective date of this AD.At intervals not to exceed 

2 years.

A detailed inspection of 

the upper and lower 

chord of the front spar 

and the lower chord of 

the rear spar from WBL 

70.5 to the wing tip for 

cracks, corrosion, minor 

surface defects, and existing stop-drilled repairs 

of cracking (initial inspection only), in accordance with paragraph 

3.B., Work Instructions, 

Part 3, of the Accomplishment Instructions of 

the service bulletin. 

(3) Group 1 ........................ Before 20 years since the 

date of issuance of the 

original Airworthiness 

Certificate or the date of 

issuance of the original 

Export Certificate of Airworthiness.

Within 4 years after the effective date of this AD.At intervals not to exceed 

4 years.

An HFEC inspection of the 

upper and lower chords 

of the rear spar from 

WBL 70.5 to the wing tip 

for cracks, corrosion, 

minor surface defects, 

and existing stop-drilled 

repairs of cracking (initial inspection only), in 

accordance with paragraph 3.B., Work Instructions, Part 4, of the 

Accomplishment Instructions of the service bulletin. 

(4) Group 1 ........................ Within 2 years after doing 

the actions required by 

paragraph (h)(1) of this 

AD.

None .................................. At intervals not to exceed 

2 years.

A detailed inspection of 

the upper chord of the 

rear spar WBL 70.5 to 

the wing tip for cracks, 

corrosion, minor surface 

defects, and existing 

stop-drilled repairs of 

cracking (initial inspection only), in accordance 

with paragraph 3.B., 

Work Instructions, Part 

8, of the Accomplishment Instructions of the 

service bulletin. 

Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations 12123

TABLE 1.—COMPLIANCE TIMES FOR INSPECTIONS SPECIFIED IN PARTS 2 THROUGH 6, AND 8 AND 9 OF SERVICE

BULLETIN—Continued

For airplanes identified in 

the service bulletin as— Threshold— Grace period— Repetitive interval— Do—

(5) Group 1 ........................ Within 4 years after doing 

the actions required by 

paragraph (h)(1) of this 

AD.

None .................................. At intervals not to exceed 

4 years.

An HFEC inspection of 

doing the not to the 

upper chord actions exceed 4 of the rear spar 

required by years from 

WBL 70.5 to paragraph 

the wing tip for (h)(1) of 

cracks, this AD corrosion, minor surface defects, and existing stopdrilled repairs of cracking (initial inspection 

only), in accordance with 

paragraph 3.B., Work Instructions, Part 9, of the 

Accomplishment Instructions of the service bulletin. 

(6) Group 2 ........................ Before 20 years since the 

date of issuance of the 

original Airworthiness 

Certificate or the date of 

issuance of the original 

Export Certificate of Airworthiness.

Within 2 years after the effective date of this AD.At intervals not to exceed 

2 years.

An exterior detailed inspection of the upper 

and lower chords of the 

front and rear spars 

from WBL 70.5 to the 

wing tip for cracks, corrosion, minor surface 

defects, and existing 

stop-drilled repairs of 

cracking (initial inspection only), in accordance 

with paragraph 3.B., 

Work Instructions, Part 

5, of the Accomplishment Instructions of the 

service bulletin. 

(7) Group 2 ........................ Before 20 years since the 

date of issuance of the 

original Airworthiness 

Certificate or the date of 

issuance of the original 

Export Certificate of Airworthiness.

Within 4 years after the effective date of this AD.At intervals not to exceed 

4 years.

An HFEC inspection of the 

upper and lower chords 

of the front and rear 

spars from WBL 70.5 to 

the wing tip for cracks, 

corrosion, minor surface 

defects, and existing 

stop-drilled repairs of 

cracking (initial inspection only), in accordance 

with paragraph 3.B., 

Work Instructions, Part 

6, of the Accomplishment Instructions of the 

service bulletin. 

Corrective Actions 

(i) If any crack, corrosion, or minor surface 

defect is detected during any inspection 

required by this AD, before further flight, do 

the applicable corrective actions in 

accordance with Part 7 of the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraph (j) 

of this AD. 

(j) If any crack or corrosion is detected 

during any inspection required by this AD 

that exceeds the limits specified in the 

service bulletin, and the bulletin specifies to 

contact Boeing for appropriate action: Before 

further flight, repair in accordance with a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

in accordance with data meeting the 

certification basis of the airplane approved 

by an Authorized Representative for the 

Boeing Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically reference this 

AD. 

(k) If any existing stop-drilled repair of 

previous cracking is detected during any 

inspection required by this AD, before further 

flight, permanently repair crack in 

accordance with paragraph 3.B., Work 

Instructions, Part 7, paragraph 2., ‘‘Crack 

Repair’’ of the Accomplishment Instructions 

of the service bulletin. 

(l) Before further flight following any 

inspection or repair required by this AD, 

apply a wet layer of BMS 3–23 organic 

corrosion inhibiting compound or Boeing 

equivalent, in accordance with the 

Accomplishment Instructions of the service 

bulletin. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle ACO, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

2002–24–05, amendment 39–12970, are 

12124 Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations 

approved as alternative methods of 

compliance with 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 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make such 

findings. For a repair method to be approved, 

the approval must specifically reference this 

AD. 

Material Incorporated by Reference 

(n) You must use Boeing Alert Service 

Bulletin 727–57A0145, Revision 2, dated 

October 24, 2002, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register previously approved the 

incorporation by reference of this document 

as of December 18, 2002 (67 FR 71808, 

December 3, 2002). For copies of the service 

information, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. For information on 

the availability of this material at the 

National Archives and Records 

Administration (NARA), call (202) 741–6030, 

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

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW, room PL–401, Nassif 

Building, Washington, DC.

Issued in Renton, Washington, on March 2, 

2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–4826 Filed 3–10–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19751; Directorate 

Identifier 2002–NM–59–AD; Amendment 39–

14001; AD 2005–05–12] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

(Jetstream) Model 4101 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all BAE 

Systems (Operations) Limited 

(Jetstream) Model 4101 airplanes. This 

AD requires repetitive detailed 

inspections of the aft fuselage frames for 

any discrepancies, and any applicable 

corrective actions. This AD is prompted 

by reports of corrosion found on the aft 

fuselage frames due to the ingress of 

water or liquid. We are issuing this AD 

to detect and correct corrosion of the aft 

fuselage frames, which could result in 

reduced structural integrity of the 

fuselage.

DATES: This AD becomes effective April 

15, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of April 15, 2005.

ADDRESSES: For service information 

identified in this AD, contact British 

Aerospace Regional Aircraft American 

Support, 13850 Mclearen Road, 

Herndon, Virginia 20171. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You can examine the 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 U.S. Department of Transportation, 

400 Seventh Street SW, room PL–401, 

Washington, DC. This docket number is 

FAA–2004–19751; the directorate 

identifier for this docket is 2002–NM–

59–AD.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR Part 39 with 

an AD for all BAE Systems (Operations) 

Limited (Jetstream) Model 4101 

airplanes. That action, published in the 

Federal Register on December 1, 2004 

(69 FR 69834), proposed to require 

repetitive detailed inspections of the aft 

fuselage frames for any discrepancies, 

and any applicable corrective actions. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the single comment that was 

submitted on the proposed AD. 

Request To Revise Discussion Section 

The commenter requests that we 

revise the Discussion section of the 

proposed AD. The commenter suggests 

that the sentence that describes the area 

where corrosion may occur should read, 

‘‘This corrosion occurs on frame areas 

below floor panel level, between frames 

434 and 555, particularly in the vicinity 

of the toilet, galley, and baggage door 

due to the ingress of water or liquid.’’

The commenter’s suggestion points out 

that, though corrosion particularly 

occurs in the vicinity of the toilet, 

galley, and baggage door, it may also 

occur over a wider area. 

We acknowledge that the 

commenter’s suggestion is accurate. 

However, the Discussion section is not 

restated in the final rule. Thus, we have 

made no change to the final rule. 

Explanation of Change to This AD 

We have revised the applicability 

statement in paragraph (c) of this AD to 

identify model designations as 

published in the most recent type 

certificate data sheet for the affected 

models. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that was submitted, and determined that 

air safety and the public interest require 

adopting the AD with the change 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD will affect about 57 airplanes 

of U.S. registry. The required 

inspections will take about 30 work 

hours per airplane, at an average labor 

rate of $65 per work hour. Based on 

these figures, the estimated cost of this 

AD for U.S. operators is $111,150, or 

$1,950 per airplane, 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.