54318 Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules 

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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Bombardier, Inc. (Formerly de Havilland, 

Inc.): Docket No. FAA–2005–20403; 

Directorate Identifier 2005–NM–144–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 14, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–400 series airplanes, certificated in 

any category; serial numbers 4001, and 4003 

through 4081 inclusive. 

Unsafe Condition 

(d) This AD results from a report indicating 

that laminated shims were delaminated and 

extruded from the interface between the 

forward attaching fittings of horizontal 

stabilizer and the top rib of the vertical 

stabilizer, and that inadequate torque values 

of some bolts were found. We are issuing this 

AD to prevent reduced structural integrity of 

the horizontal stabilizer, and consequent loss 

of controllability of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Service Information 

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

this AD, means the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–55–02, Revision ‘A,’ dated January 12, 

2005. 

(g) Accomplishing a detailed inspection, a 

breakaway torque check, and corrective 

actions if necessary before the effective date 

of this AD in accordance with Bombardier 

Service Bulletin 84–55–02, dated December 

11, 2003, is acceptable for compliance with 

the corresponding requirements of this AD. 

(h) Accomplishing the repair before the 

effective date of this AD in accordance with 

the Bombardier repair drawings in Table 1 of 

this AD is acceptable for compliance with the 

requirements of this AD. 

TABLE 1.—REPAIR DRAWINGS

Bombardier 

repair drawing 

RD 

issue Dated 

RD 8/4–55–083 3 April 16, 2003. 

RD 8/4–55–084 1 May 5, 2003. 

RD 8/4–55–089 2 June 6, 2003. 

RD 8/4–55–090 3 August 26, 

2003. 

RD 8/4–55–093 2 June 20, 2003. 

RD 8/4–55–094 3 September 4, 

2003. 

RD 8/4–55–106 2 July 31, 2003. 

RD 8/4–55–110 3 October 1, 2003. 

RD 8/4–55–138 1 October 29, 

2003. 

Detailed Inspection and Torque Check 

(i) Within 4,000 flight hours after the 

effective date of this AD, do the actions 

specified in paragraphs (i)(1) and (i)(2) of this 

AD in accordance with Part A of the service 

bulletin. 

(1) Do a detailed inspection of the 

laminated shims for cracks, damage, or 

extrusion between the forward attachment 

fittings of the horizontal stabilizer and the 

top rib of the vertical stabilizer. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(2) Do a breakaway torque check of the six 

attachment bolts in the attachment fittings of 

the front, middle, and rear spars. 

Corrective Actions 

(j) If, during the inspection required by 

paragraph (i)(1) of this AD, any cracked, 

damaged, or extruded laminated shim is 

found, before further flight, replace the 

discrepant laminated shim with a solid shim, 

and replace the attachment bolts, barrel nuts, 

and retainers of both front spars with new 

parts, in accordance with Parts A and B of 

the service bulletin. 

(k) If, during the torque check required by 

paragraph (i)(2) of this AD, any attachment 

bolt is found with a breakaway torque value 

outside the limits specified in the service 

bulletin, before further flight, replace the 

attachment bolt and its corresponding barrel 

nut and retainer with new parts, in 

accordance with Part A of the service 

bulletin. 

Replacement of Laminated Shims 

(l) Within 8,000 flight hours after the 

effective date of this AD, unless previously 

accomplished in accordance with paragraph 

(j) of this AD, replace the laminated shims, 

between the forward attachment fittings of 

the horizontal stabilizer and the top rib of the 

vertical stabilizer, with solid shims and 

replace the corresponding barrel nut and 

retainer with new parts, in accordance with 

Part B of the service bulletin. 

No Reporting 

(m) Although the service bulletin 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(n) The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(o) Canadian airworthiness directive CF–

2005–07, issued March 21, 2005, also 

addresses the subject of this AD. 

Issued in Renton, Washington, on 

September 6, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18208 Filed 9–13–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20402; Directorate 

Identifier 2005–NM–133–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sabreliner 

Model NA–265, NA–265–20, NA–265–

30, NA–265–40, NA–265–50, NA–265–

60, NA–265–65, NA–265–70, and NA–

265–80 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Sabreliner Model NA–265–40, NA–265–

50, NA–265–60, NA–265–70, and NA–

265–80 series airplanes. The existing 

AD currently requires repetitive 

inspections for discrepancies in the 

front and rear spars of the wing in the 

area of the wing center section, and in 

the lugs on the rear spar and wing 

trailing edge panel rib, and corrective 

actions if necessary. This proposed AD 

would expand the applicability of the 

existing AD and require new repetitive 

inspections for fuel leaks of the front 

Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules 54319 

and rear spars of the wing, and for 

discrepancies in the front and rear spars 

of the wing in the area of the wing 

center section, and in the lugs on the 

rear spar and wing trailing edge panel 

rib. This proposed AD would also 

require related investigative and 

corrective actions, if necessary. This 

proposed AD results from reports of 

cracking in the upper and lower flanges 

of the front and rear spars of the wing 

near the wing center section, and in the 

lugs on the rear spar. We are proposing 

this AD to detect and correct cracking or 

other discrepancies in these areas, 

which could result in structural failure 

of the wing. 

DATES: We must receive comments on 

this proposed AD by October 31, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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 Sabreliner Corporation, 18118 

Chesterfield Airport Road, Chesterfield, 

Missouri 63005–1121, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer, Airframe 

Branch, ACE–118W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; 

telephone (316) 946–4155; fax (316) 

946–4407. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2005–20402; 

Directorate Identifier 2005–NM–133–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of that Web 

site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or may visit http:// 

dms.dot.gov. 

Examining the Docket 

You may 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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

We previously issued AD 73–18–03, 

amendment 39–3201 (43 FR 19208, May 

4, 1978), for certain Rockwell 

International Model NA–265–40, NA–

265–50, NA–265–60, NA–265–70, and 

NA–265–80 series airplanes. That AD 

requires repetitive inspections for 

discrepancies in the front and rear spars 

of the wing in the area of the wing 

center section, and in the lugs on the 

rear spar and wing trailing edge panel 

rib, and corrective actions if necessary. 

That AD resulted from reports of 

cracking in the upper and lower flanges 

of the front and rear spars of the wing 

near the wing center section, and in the 

lugs on the rear spar. We issued that AD 

to detect possible cracks, corrosion, or 

breaks in the surface finish in the wing 

spars and related areas. 

Actions Since Existing AD Was Issued 

Since we issued AD 73–18–03, we 

have determined that Sabreliner Model 

NA–265, NA–265–20, NA–265–30, and 

NA–265–65 series airplanes may also be 

subject to the unsafe condition 

addressed by AD 73–18–03. These 

models were not listed in the 

applicability statement of AD 73–18–03. 

Relevant Service Information 

We have reviewed Sabreliner NA–265 

Service Bulletin 83–2, revised January 

31, 2005. Sabreliner NA–265 Service 

Bulletin 83–2 supersedes Sabreliner 

Service Bulletin 73–11, revised June 1, 

1978. (AD 73–18–03 refers to the 

original issue of Sabreliner Service 

Bulletin 73–11, dated June 18, 1973 (or 

later FAA-approved revisions), as the 

appropriate source of service 

information for the actions required by 

that AD.) 

The procedures in Sabreliner NA–265 

Service Bulletin 83–2 are substantially 

similar to those in Sabreliner Service 

Bulletin 73–11 and specify the 

following actions: 

• Performing repetitive inspections of 

the front and rear spars of the wing for 

fuel leaks. 

• Performing repetitive inspections 

using a borescope to detect breaks in the 

surface finish, cracking, or corrosion in 

the upper and lower flanges of the front 

spar of the wing, in the area of the wing 

center section. 

• Performing repetitive inspections 

using a borescope to detect breaks in the 

surface finish, cracking, or corrosion in 

the upper and lower flanges and the 

splice plates of the rear spar of the wing, 

in the area of the wing center section. 

• Performing related investigative 

action, consisting of a penetrant 

inspection for cracking, if a break in the 

surface finish or corrosion is found 

during any inspection of the rear spar in 

the area of the wing center section. 

• Performing repetitive inspections to 

detect cracking in the lugs of the 

outboard rear spar and in the fittings on 

the wing trailing edge panel rib. 

• Contacting Sabreliner for an 

engineering analysis if any crack, 

corrosion, or break in the surface finish 

is found. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 73–18–

03 and would retain the requirements of 

the existing AD. This proposed AD 

would also expand the applicability to 

include additional airplanes, and would 

require accomplishing the actions 

specified in Sabreliner NA–265 Service 

Bulletin 83–2, revised January 31, 2005, 

except as discussed under ‘‘Differences 

Between the Proposed AD and Service 

Information.’’

54320 Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules 

Differences Between the Proposed AD 

and Service Information 

Sabreliner NA–265 Service Bulletin 

83–2, revised January 31, 2005, specifies 

that operators may contact the 

manufacturer for disposition of certain 

repair conditions. This proposed AD 

would require operators to repair those 

conditions in accordance with a method 

approved by the FAA. 

Sabreliner NA–265 Service Bulletin 

83–2, revised January 31, 2005, specifies 

an inspection for fuel leaks, and another 

inspection for cracking of the lugs on 

the rear spar and wing trailing edge 

panel rib. We have determined that 

these inspections can be done using a 

general visual inspection method. Note 

1 of this proposed AD defines a general 

visual inspection. 

Sabreliner NA–265 Service Bulletin 

83–2, revised January 31, 2005, 

describes procedures for submitting a 

sheet recording compliance with the 

service bulletin. This proposed AD does 

not require that action. 

These differences have been 

coordinated with the manufacturer. 

Changes to Existing AD 

The FAA has revised the applicability 

of the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Also, we removed all references to 

‘‘later FAA-approved revision’’ from the 

requirements of the existing AD, to be 

consistent with the policy of the Office 

of the Federal Register. This change will 

not increase the economic burden on 

any operator, nor will it increase the 

scope of the AD, since we may decide 

to approve later revisions of the service 

bulletin as an alternative method of 

compliance with this AD, as provided 

by paragraph (n) of this AD. 

Also, we have revised references to 

inspecting and doing repairs in 

accordance with a method ‘‘approved by 

the Chief, Aircraft Engineering Division, 

FAA Western Region.’’ This office no 

longer exists. Accordingly, we have 

revised paragraphs (f), (g), and (h) of this 

AD to refer to inspecting and doing 

repairs, as applicable, in accordance 

with a method approved by the 

Manager, Wichita Aircraft Certification 

Office, FAA. We have also included 

paragraph (i) in this proposed AD to 

give credit for inspecting or doing 

repairs before the effective date of this 

AD in accordance with a method 

approved by the Chief, Aircraft 

Engineering Division, FAA Western 

Region. 

Costs of Compliance 

There are about 77 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 43 

airplanes of U.S. registry. 

The inspection specified in this 

proposed AD would take about 12 work 

hours per airplane, per inspection cycle, 

at an average labor rate of $65 per work 

hour. Based on these figures, the 

estimated cost of the new actions 

specified in this proposed AD for U.S. 

operators is $33,540, or $780 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. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 39–3201 (43 

FR 19208, May 4, 1978) and adding the 

following new airworthiness directive 

(AD): 

Sabreliner Corporation: Docket No. FAA–

2005–20402; Directorate Identifier 2005–

NM–133–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 31, 2005. 

Affected ADs 

(b) This AD supersedes AD 73–18–03. 

Applicability 

(c) This AD applies to Sabreliner Model 

NA–265, NA–265–20, NA–265–30, NA–265–

40, NA–265–50, NA–265–60, NA–265–65, 

NA–265–70, and NA–265–80 series 

airplanes; certificated in any category; as 

identified in Sabreliner NA–265 Service 

Bulletin 83–2, revised January 31, 2005. 

Unsafe Condition 

(d) This AD results from reports of cracking 

in the upper and lower flanges of the front 

and rear spars of the wing near the wing 

center section, and in the lugs on the rear 

spar. The FAA is issuing this AD to detect 

and correct cracking or other discrepancies in 

these areas, which could result in structural 

failure 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. 

Requirements of AD 73–18–03 

Repetitive Inspections 

(f) For the airplanes listed in Table 1 of this 

AD: On or before June 18, 1974, unless 

previously accomplished within 1 year, and 

at intervals not to exceed 2 years thereafter 

until the first inspection in accordance with 

paragraph (j) of this AD has been done, 

inspect the upper and lower flanges of the 

front and rear spars in the area of the wing 

center section, and the lugs on the rear spar 

and wing trailing edge panel rib, per the 

instructions of Sabreliner Service Bulletin 

Federal Register / Vol. 70, No. 177 / Wednesday, September 14, 2005 / Proposed Rules 54321 

73–11, revised June 1, 1978; or an equivalent 

inspection approved by the Manager, Wichita 

Aircraft Certification Office (ACO), FAA. 

Inspections done before the effective date of 

this AD in accordance with Sabreliner 

Service Bulletin 73–11, dated June 15, 1973, 

are acceptable for compliance with this 

paragraph. 

TABLE 1.—AIRPLANES SUBJECT TO

PARAGRAPH (F), (G), AND (H) OF

THIS AD 

Model Affected serial numbers 

NA–265–40 ......... 282–1 and subsequent. 

NA–265–50 ......... 287–1. 

NA–265–60 ......... 306–1 through 306–139 

inclusive. 

NA–265–70 ......... 370–1 through 370–9 inclusive. 

NA–265–80 ......... 380–1 through 380–61 inclusive. 

Corrective Actions 

(g) For the airplanes listed in Table 1 of 

this AD: Prior to further flight, if cracks, 

corrosion, or breaks in the surface finish are 

found, during any inspection in accordance 

with paragraph (f) of this AD, in the front or 

rear spars in the area of the wing center 

section, replace with like serviceable parts, or 

repair in a manner approved by the Manager, 

Wichita ACO. 

(h) For the airplanes listed in Table 1 of 

this AD: Prior to further flight, if cracks are 

found, during any inspection in accordance 

with paragraph (f) of this AD, in the lugs on 

the rear spar and wing trailing edge rib, 

replace the cracked parts with like 

serviceable parts, or repair in a manner 

approved by the Manager, Wichita ACO. 

New Requirements of This AD 

Inspections/Repairs Accomplished 

Previously 

(i) Inspections and repairs accomplished 

before the effective date of this AD in 

accordance with a method approved by the 

Chief, Aircraft Engineering Division, FAA 

Western Region, are acceptable for 

compliance with paragraphs (f), (g), and (h) 

of this AD, as applicable. 

New Repetitive Inspections 

(j) Within 90 days after the effective date 

of this AD, except as provided by paragraph 

(j)(1) of this AD: Perform a general visual 

inspection for fuel leaks; an inspection using 

a borescope to detect any break in the surface 

finish, corrosion, or cracking of the upper 

and lower flanges on the front and rear spars 

of the wing in the area of the wing center 

section; a general visual inspection to detect 

cracking of the lugs on the rear spar and wing 

trailing edge panel rib; and related 

investigative actions, as applicable; by doing 

all applicable actions in accordance with the 

instructions of Sabreliner NA–265 Service 

Bulletin 83–2, revised January 31, 2005. 

Repeat the inspection thereafter at intervals 

not to exceed 24 months. 

(1) If the inspection required by paragraph 

(j) of this AD has been accomplished within 

12 months before the effective date of this 

AD, the inspection required by paragraph (j) 

of this AD is not required until 24 months 

after the most recent inspection in 

accordance with the requirements of 

paragraph (j) of this AD. 

(2) For airplanes subject to paragraph (f) of 

this AD: Accomplishing of the initial 

inspection required by paragraph (j) of this 

AD terminates the requirements of paragraph 

(f) of this AD. 

Note 1: 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.’’

Corrective Actions 

(k) If any fuel leak, break in the surface 

finish, corrosion, or cracking is found during 

any inspection required by paragraph (j) of 

this AD: Before further flight, replace the 

subject part with a new or serviceable part, 

or repair the subject part in accordance with 

a method approved by the Manager, Wichita 

ACO. Where Sabreliner NA–265 Service 

Bulletin 83–2 specifies contacting Sabreliner 

for an engineering analysis: Before further 

flight, repair in accordance with a method 

approved by the Manager, Wichita ACO. For 

a repair method to be approved by the 

Manager, Wichita ACO, as required by this 

paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

Actions Accomplished Previously 

(l) Inspections and corrective actions 

accomplished before the effective date of this 

AD in accordance with the original issue of 

Sabreliner NA–265 Service Bulletin 83–2, 

dated March 4, 1983; or Sabreliner NA–265 

Service Bulletin 83–2, revised February 29, 

1996; are acceptable for compliance with the 

corresponding actions required by 

paragraphs (j) and (k) of this AD. 

No Reporting Requirement 

(m) Although the service bulletin 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(n) The Manager, Wichita ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

Issued in Renton, Washington, on 

September 6, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18209 Filed 9–13–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22411; Directorate 

Identifier 2005–NM–074–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 Series Airplanes; Model A300 

B4 Series Airplanes; Model A300 B4–

600 Series Airplanes; Model A300 B4–

600R Series Airplanes; Model F4 600R 

Series Airplanes; Model A300 C4–605R 

Variant F Airplanes; and Model A310–

200 Series Airplanes; and Model A310–

300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus transport category 

airplanes. This proposed AD would 

require replacing the existing cabin 

altitude indicator in the cabin pressure 

control panel with a new, improved 

cabin altitude indicator. This proposed 

AD is prompted by a report of injuries 

occurring on in-service airplanes when 

crewmembers forcibly initiated opening 

of passenger/crew doors against residual 

pressure causing the doors to rapidly 

open. We are proposing this AD to 

prevent injury to crewmembers, and 

subsequent damage to the airplane 

caused by rapid opening of the door. 

DATES: We must receive comments on 

this proposed AD by October 14, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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. 

• By 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. 

For service information identified in 

this proposed AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France.