This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

70048 

Vol. 70, No. 223 

Monday, November 21, 2005 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23007; Directorate 

Identifier 2005–NM–013–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–200 and –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 Model A310–200 and 

–300 series airplanes. This proposed AD 

would require repetitive inspections for 

cracks and corrosion of the areas behind 

the scuff plates below the passenger/ 

crew doors and bulk cargo door, and 

repair of any cracked or corroded part. 

This proposed AD also would require 

repetitive inspections for cracks of the 

holes of the corner doublers, the failsafe ring, and the door frames of the 

passenger/crew door structures. This 

proposed AD is prompted by reports of 

corrosion behind the scuff plates at 

passenger/crew doors and the bulk 

cargo door and fatigue cracks on the 

corner doublers of the forward and aft 

passenger/crew door frames. We are 

proposing this AD to prevent such 

corrosion and fatigue cracking, which 

could result in reduced structural 

integrity of the door surroundings. 

DATES: We must receive comments on 

this proposed AD by December 21, 

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. 

You can examine the contents of this 

AD docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2005– 

23007; the directorate identifier for this 

docket is 2005–NM–013–AD. 

FOR FURTHER INFORMATION CONTACT: 

Rosanne Ryburn, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2139; 

fax (425) 227–1149. 

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 under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2005–23007; Directorate Identifier 

2005–NM–013–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 submitted 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 our docket 

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 can 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you can visit http:// 

dms.dot.gov. 

Examining the Docket 

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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

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 on certain Airbus Model A310–200 

and –300 series airplanes. The DGAC 

advises that it received reports 

indicating that corrosion was found 

behind the scuff plates at passenger/ 

crew doors and the bulk cargo door. The 

DGAC also advises that results of 

structural fatigue testing have revealed 

that cracks were found on the corner 

doublers of the forward and aft 

passenger/crew door frames; and, after 

various simulated flights, on the failsafe ring and frames 14 and 16A of the 

forward passenger/crew door. After 

50,000 simulated flights, cracks 

measuring between 8.0 millimeters 

(mm) and 109.0 mm were found on the 

forward door frames and fail-safe ring. 

After 60,493 simulated flights, a 53.0 

mm crack was found on the mid door 

frame. After 106,000 simulated flights, a 

32.0 mm crack was found on the aft 

door frame. In all cases, the cracks 

originated at the fastener holes. In 

addition, cracks originating from corner 

doubler edges were found at the aft 

passenger/crew doors. 

Such corrosion and fatigue cracking, 

if not detected and corrected, could 

result in reduced structural integrity of 

the door surroundings. 

Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Proposed Rules 70049 

Other Relevant Rulemaking 

We have previously issued AD 97–

11–03, amendment 39–10032 (62 FR 

28325, May 23, 1997), applicable to all 

Airbus Model A300 series airplanes. 

That AD requires inspections of the 

lower door surrounding structure to 

detect cracks and corrosion; inspections 

to detect cracking of the holes of the 

corner doublers, the fail-safe ring, and 

the door frames of the door structures; 

and repair if necessary. That AD also 

requires modification of the passenger/ 

crew door frames, which terminates 

certain inspections. 

We also previously issued AD 98–16–

05, amendment 39–10680 (63 FR 40812, 

July 31, 1998), applicable to all Airbus 

Model A300–600 series airplanes. That 

AD requires inspections of the areas 

behind the scuff plates below the 

passenger/crew doors and bulk cargo 

door to detect cracks and corrosion; 

inspections to detect cracking of the 

holes of the corner doublers, the failsafe ring, and the door frames of the 

door structures; and repair if necessary. 

In addition, that AD provides for an 

optional terminating action for certain 

inspections. We are considering further 

rulemaking to mandate the optional 

terminating action. 

Relevant Service Information 

Airbus has issued the service 

bulletins in the following table: 

SERVICE BULLETINS

Airbus Service Bulletin— Describes procedures for— 

A310–53–2030, Revision 06, dated July 2, 1996 .................................... Doing initial inspections for cracks and corrosion of the areas behind 

the scuff plates below the passenger/crew doors and bulk cargo 

door, and repairing any cracked or corroded part. 

A310–53–2041, Revision 02, dated July 2, 1996 .................................... Doing repetitive inspections for cracks and corrosion of the areas behind the scuff plates below the passenger/crew doors and bulk cargo 

door, and repairing any cracked or corroded part. 

A310–53–2037, Revision 02, dated November 27, 2000 ........................ Doing repetitive inspections for cracks of the holes of the corner doublers, the fail-safe ring, and the door frames of the passenger/crew 

door structures, and repairing any cracked part. 

A310–53–2017, Revision 09, dated May 17, 2004 .................................. Modifying the passenger/crew door structures, which ends the repetitive inspections of the holes of the corner doublers, fail-safe ring, 

and the door frames for certain airplanes. The modification includes 

cold expansion of fastener holes; a ROTO test; installation of new 

oversize fasteners and modified brackets; and installation of an additional steel doubler. 

Accomplishing the actions specified in 

the service information is intended to 

adequately address the unsafe 

condition. The DGAC mandated the 

service information and issued French 

airworthiness directives 1991–132–

124(B) R1, issued November 29, 2000, 

and F–2004–103, issued July 7, 2004, to 

ensure the continued airworthiness of 

these airplanes in France. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require accomplishing the 

applicable actions specified in the 

service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD, 

French Airworthiness Directive, and 

Service Bulletins.’’

Differences Between the Proposed AD, 

French Airworthiness Directive, and 

Service Bulletins 

Airbus Service Bulletin A310–53–

2030 also does not list a grace period for 

certain compliance times. This 

proposed AD adds a grace period to 

certain compliance times. We find that 

a grace period will keep airplanes from 

being grounded unnecessarily. 

Airbus Service Bulletins A310–53–

2041 and A310–53–2037 specify 

repetitive inspections at ‘‘every’’

specified interval; however, this 

proposed AD would require compliance 

‘‘at intervals not to exceed’’ the time 

specified in the service bulletin. These 

service bulletins also specify 

compliance times in ‘‘flights.’’ This 

proposed AD would specify those times 

as flight cycles. In addition, Airbus 

Service Bulletin A310–53–2037 does 

not specify a starting date for the 

threshold for the initial inspections. 

This proposed AD would require 

compliance before the specified 

compliance time after the effective date 

of this AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. The 

average labor rate per hour is $65. 

ESTIMATED COSTS

Action Work hours Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Initial inspections behind scuff 

plates (for all airplanes).

26 ............................. None ......................... $1,690 ...................... 46 $77,740. 

Repetitive inspections behind 

scuff plates, per inspection 

cycle (for all airplanes).

26 ............................. None ......................... $1,690 ...................... 46 $77,740, per inspection cycle. 

70050 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Proposed Rules 

ESTIMATED COSTS—Continued 

Action Work hours Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections of corner doublers, 

fail-safe ring, and door 

frames, per inspection cycle.

Between 4 and 50 

depending on kit 

purchased.

None ......................... Between $260 and 

$3,250.

46 Between $11,960, 

and $149,500 per 

inspection cycle. 

Terminating modification for repetitive inspection of corner 

doublers, fail-safe ring, and 

door frames.

Between 8 and 55 

depending on kit 

purchased.

Between $506 and 

$6,098 depending 

on kit purchased.

Between $1,026 and 

$9,673.

46 Between $47,196 

and $444,958. 

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 

0130132. 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. 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), 401013, 44701. 

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Airbus: Docket No. FAA–2005–23007; 

Directorate Identifier 2005–NM–013–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by December 21, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310–

203, –204, –221, and –222 airplanes; and 

Airbus Model A310–304, –322, –324, and 

–325 airplanes; certificated in any category; 

excluding those airplanes on which Airbus 

Modification 5068, 7201, and 7298 have been 

incorporated in production. 

Unsafe Condition 

(d) This AD was prompted by reports of 

corrosion behind the scuff plates at 

passenger/crew doors and the bulk cargo 

door and fatigue cracks on the corner 

doublers of the forward and aft passenger/ 

crew door frames. We are issuing this AD to 

prevent such corrosion and fatigue cracking, 

which could result in reduced structural 

integrity of the door surroundings. 

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. 

Initial Inspections Behind Scuff Plates 

(f) Do initial inspections (i.e., nondestructive tests) for cracks and corrosion of 

the areas behind the scuff plates below the 

passenger/crew doors and bulk cargo door, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

53–2030, Revision 06, dated July 2, 1996. Do 

the inspections at the applicable time 

specified in paragraphs (f)(1) and (f)(2) of 

Table 1 of this AD. If a records check cannot 

positively identify if the applicable 

modification or service information specified 

in paragraphs (f)(1) and (f)(2) of this AD has 

been done, assume that it has not. 

TABLE 1.—COMPLIANCE TIME REQUIREMENTS FOR INITIAL INSPECTIONS BEHIND SCUFF PLATES

For airplanes on which Modification 5382S6526 

for the forward doors and Modification 

5382D4741 for all other doors—

And— Inspect—

(1) Have been incorporated in production ......... None ................................................................. Within 108 months after first flight. 

(2) Have not been incorporated in production ... (i) Airbus Service Information Letter (SIL) 

A300–53–033, Revision 2, dated November 

23, 1984, for all doors, was not followed; or 

Airbus Service Bulletin A310–53–2004, Revision 2, March 9, 1984 (only applicable for 

the forward doors), was not done.

Within 48 months since the date of issuance 

of the original standard Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, or 

within 12 months after the effective date of 

this AD, whichever occurs later. 

Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Proposed Rules 70051 

TABLE 1.—COMPLIANCE TIME REQUIREMENTS FOR INITIAL INSPECTIONS BEHIND SCUFF PLATES—Continued 

For airplanes on which Modification 5382S6526 

for the forward doors and Modification 

5382D4741 for all other doors—

And— Inspect—

(ii) Airbus SIL A300–53–033, Revision 2, 

dated November 23, 1984, for all doors, 

was followed; or Airbus Service Bulletin 

A310–53–2004, Revision 2, dated March 9, 

1984 (only applicable for the forward 

doors), was done.

Within 60 months since the date of issuance 

of the original Airworthiness Certificate or 

the date of issuance of the original Export 

Certificate of Airworthiness, or within 12 

months after the effective date of this AD, 

whichever occurs later. 

(iii) Airbus SIL A300–53–033, Revision 2, 

dated November 23, 1984, for all doors, 

was followed; or Airbus Service Bulletin 

A310–53–2004, Revision 2, dated March 9, 

1984 (only applicable for the forward 

doors), was done more than 48 months ago 

as of the effective date of this AD.

Within 12 months after the effective date of 

this AD. 

Repetitive Inspections Behind Scuff Plates 

(g) Following the initial inspection 

required by paragraph (f) of this AD, do 

repetitive inspections (i.e., non-destructive 

tests) for cracks and corrosion of the areas 

behind the scuff plates below the passenger/ 

crew doors and bulk cargo door, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

53–2041, Revision 02, dated July 2, 1996. 

Repeat the inspections at the applicable 

times specified in paragraphs (g)(1) through 

(g)(4) of Table 2 of this AD. 

TABLE 2.—COMPLIANCE TIME REQUIREMENTS FOR REPETITIVE INSPECTIONS BEHIND SCUFF PLATES

For— At— Inspect at intervals not to 

exceed—

Unless in case of corrosion 

removal, then inspect at intervals not to exceed—

(1) All airplanes ................... The forward passenger/crew doors and the bulk cargo 

door.

60 months .......................... None. 

(2) All airplanes ................... The aft passenger/crew doors, except the upper and 

lower edges of the door frame panel cutout.

60 months .......................... None. 

(3) Model A310–203, –204, 

–221, and –222 airplanes.

The aft passenger/crew doors, the upper and lower 

edges of the door frame panel cutout.

60 months or 12,000 flight 

cycles, whichever occurs 

first.

60 months or 9,600 flight 

cycles, whichever occurs 

first. 

(4) Model A310–304, –322, 

–324, and –325 airplanes.

The aft passenger/crew doors, the upper and lower 

edges of the door frame panel cutout.

60 months or 7,000 flight 

cycles, whichever occurs 

first.

60 months or 5,600 flight 

cycles, whichever occurs 

first. 

Repetitive Inspections of Corner Doublers, 

Fail-Safe Ring, and Door Frames 

(h) Do inspections (i.e., rotating probe, xray, and general visual, as applicable) for 

cracks of the holes of the corner doublers, the 

fail-safe ring, and the door frames of the 

passenger/crew door structures, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310–

53–2037, Revision 02, dated November 27, 

2000. Do the inspections at the applicable 

times specified in paragraphs (h)(1) through 

(h)(3) of Table 3 of this AD, until the 

modification required by paragraph (k) of this 

AD is done. 

TABLE 3.—COMPLIANCE TIME REQUIREMENTS FOR REPETITIVE INSPECTIONS OF CORNER DOUBLERS, FAIL-SAFE RING, 

AND DOOR FRAMES

For— Inspect— And—

(1) The upper corners of the forward doors ....... Before the accumulation of 20,000 total flight 

cycles, or within 2,000 flight cycles after the 

effective date of this AD, whichever occurs 

later.

Do rotating probe inspections at intervals not 

to exceed 6,000 flight cycles. 

(2) The lower corners of the forward doors ....... Before the accumulation of 20,000 total flight 

cycles, or within 4,000 flight cycles after the 

effective date of this AD, whichever occurs 

later.

Do rotating probe inspections at intervals not 

to exceed 10,000 flight cycles. 

(3) The upper and lower corners and parts underneath the corners of the upper door 

frames of the aft doors.

Before the accumulation of 20,000 total flight 

cycles, or within 4,000 flight cycles after the 

effective date of this AD, whichever occurs 

later.

Do rotating probe inspections at intervals not 

to exceed 8,000 flight cycles or do x-ray inspections at intervals not to exceed 3,500 

flight cycles; and do general visual inspections of areas around fasteners in vicinity of 

stringer 12 of the upper door frames at intervals not to exceed 6,900 flight cycles. 

70052 Federal Register / Vol. 70, No. 223 / Monday, November 21, 2005 / Proposed Rules 

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 

(i) If any crack or corrosion is found during 

any inspection required by this AD, before 

further flight, do the applicable corrective 

action in paragraph (i)(1) through (i)(3) of 

Table 4 of this AD, except as provided by 

paragraph (j) of this AD. 

TABLE 4.—CORRECTIVE ACTIONS

If— Then— In accordance with the accomplishment instructions of—

(1) Any crack or corrosion is found during any 

inspection required by paragraph (f) of this 

AD.

Repair the cracked or corroded part ............... Airbus Service Bulletin A310–53–2030, Revision 06, dated July 2, 1996. 

(2) Any crack or corrosion is found during any 

repetitive inspection required by paragraph 

(g) of this AD.

Repair the cracked or corroded part ............... Airbus Service Bulletin A310–53–2041, Revision 02, dated July 2, 1996. 

(3) Any crack is found during any inspection required by paragraph (h) of this AD.Repair the cracked part ................................... Airbus Service Bulletin A310–53–2037, Revision 02, dated November 27, 2000. 

(j) If any crack or corrosion is found during 

any inspection required by this AD, and the 

service bulletin recommends contacting 

Airbus for appropriate action: Before further 

flight, repair the cracked or corroded part in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent). 

Terminating Modification for Repetitive 

Inspection of Corner Doublers, Fail-Safe 

Ring, and Door Frames 

(k) Modify the passenger/crew door 

structures in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–53–2017, Revision 09, 

dated May 17, 2004. Do the modification at 

the applicable time in paragraph (k)(1) or 

(k)(2) of Table 5 of this AD. Accomplishment 

of this modification constitutes terminating 

action for the repetitive inspections required 

by paragraph (h) of this AD. The inspections 

required by paragraph (f) of this AD must be 

done before accomplishing this modification. 

TABLE 5.—COMPLIANCE TIME FOR TERMINATING MODIFICATION

For model— Compliance time 

(1) A310–203, –204, –221, and –222 airplanes ...................................... Before the accumulation of 40,000 flight cycles since the date of 

issuance of the original standard Airworthiness Certificate or the date 

of issuance of the original Export Certificate of Airworthiness, or during the next inspection required by paragraph (h) of this AD, whichever occurs later. 

(2) A310–304, –322, –324, and –325 airplanes ...................................... Before the accumulation of 35,000 flight cycles since the date of 

issuance of the original standard Airworthiness Certificate or the date 

of issuance of the original Export Certificate of Airworthiness, or during the next inspection required by paragraph (h) of this AD, whichever occurs later. 

Alternative Methods of Compliance 

(AMOCs) 

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

ANM–116, FAA, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(m) French airworthiness directives 1991–

132–124(B) R1, issued November 29, 2000, 

and F–2004–103, issued July 7, 2004, also 

address the subject of this AD. 

Issued in Renton, Washington, on 

November 9, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22971 Filed 11–18–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[CGD01–05–094] 

Navigation and Waterways 

Management Improvements, 

Providence River Regulated Navigation 

Area; Narragansett Bay, Rhode Island 

and Mt. Hope Bay, MA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice; request for public 

comments. 

SUMMARY: The First Coast Guard District 

announces that it is considering 

changing, rescinding, or maintaining 

certain navigation regulations currently 

in effect for the Providence River, and