### 83662 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations

under the criteria of the Regulatory Flexibility Act.

We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 adding the following new airworthiness directive (AD): 2016–23–09 Various Restricted Category Helicopters: Amendment 39–18716; Docket No. FAA–2015–3820; Directorate Identifier 2014–SW–024–AD.
(a) Applicability

This AD applies to Model TH–1F, UH–1B, UH–1F, UH–1H, and UH–1P helicopters with a main rotor (M/R) blade, part number 204– 011–250–005 or 204–011–250–113, installed.
(b) Unsafe Condition

This AD defines the unsafe condition as a crack in an M/R blade, which could result in failure of the M/R blade and subsequent loss of helicopter control.
(c) Effective Date

This AD becomes effective December 27,
2016. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

(1) Within 25 hours time-in-service (TIS) or 2 weeks, whichever occurs first, and thereafter at intervals not to exceed 25 hours TIS or 2 weeks, whichever occurs first, clean the upper and lower exposed surfaces of each M/R blade from an area starting at the butt end of the blade to three inches outboard of the doublers. Using a 3X or higher power magnifying glass and a light, inspect as follows:

(i) Visually inspect the exposed area of the lower grip pad and upper and lower grip plates of each M/R blade for a crack and any corrosion.

(ii) On the upper and lower exposed surfaces of each M/R blade from blade stations 24.5 to 35 for the entire chord width, visually inspect each layered doubler and blade skin for a crack and any corrosion. Pay particular attention for any cracking in a doubler or skin near or at the same blade station as the blade retention bolt hole (blade station 28).

(iii) Visually inspect the exposed areas of each bond line at the edges of the lower grip pad, upper and lower grip plates, and each layered doubler (bond lines) on the upper and lower surfaces of each M/R blade for the entire length and chord width for an edge void, any corrosion, loose or damaged adhesive squeeze-out, and an edge delamination. Pay particular attention to any crack in the paint finish that follows the outline of a grip pad, grip plate, or doubler, and to any loose or damaged adhesive squeeze-out, as these may be the indication of an edge void.

(2) If there is a crack, any corrosion, an edge void, loose or damaged adhesive squeeze-out, or an edge delamination during any inspection in paragraph (e)(1) of this AD, before further flight, do the following:

(i) If there is a crack in a grip pad or any grip plate or doubler, replace the M/R blade with an airworthy M/R blade.

(ii) If there is a crack in the M/R blade skin that is within maximum repair damage limits, repair the M/R blade. If the crack exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/ R blade.

(iii) If there is any corrosion within maximum repair damage limits, repair the M/ R blade. If the corrosion exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/R blade.

(iv) If there is an edge void in the grip pad or in a grip plate or doubler, determine the length and depth using a feeler gauge. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade.

(v) If there is an edge void in a grip plate or doubler near the outboard tip, tap inspect the affected area to determine the size and shape of the void. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade.

(vi) If there is any loose or damaged adhesive squeeze-out along any of the bond lines, trim or scrape away the adhesive without damaging the adjacent surfaces or parent material of the M/R blade. Determine if there is an edge void or any corrosion by lightly sanding the trimmed area smooth using 280 or finer grit paper. If there is no edge void or corrosion, refinish the sanded

area.

(vii) If there is an edge delamination along any of the bond lines or a crack in the paint finish, determine if there is an edge void or a crack in the grip pad, grip plate, doubler, or skin by removing paint from the affected area by lightly sanding in a span-wise direction using 180–220 grit paper. If there are no edge voids and no cracks, refinish the sanded area.

(viii) If any parent material is removed during any sanding or trimming in paragraphs (e)(2)(vi) or (e)(2)(vii) of this AD, repair the M/R blade if the damage is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (f) Special Flight Permits Special flight permits are prohibited.
(g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone 817– 222–5140; email 9-ASW-FTW-AMOCRequests@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(h) Additional Information

Bell Helicopter Alert Service Bulletin (ASB) No. UH–1H–13–09, dated January 14, 2013, and Bell Helicopter Textron ASB No. 204–75–1 and ASB 205–75–5, both Revision C and both dated April 25, 1979, which are not incorporated by reference, contain additional information about the subject of this final rule. For service information identified in this final rule, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280–3391; fax (817) 280–6466; or at http:// www.bellcustomer.com/files/. You may review a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177.
(i) Subject

Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades.

Issued in Fort Worth, Texas, on November 4, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2016–27767 Filed 11–21–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–4223; Directorate Identifier 2015–NM–108–AD; Amendment**  **39–18693; AD 2016–22–04]**

**RIN 2120–AA64**

**Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain


### 83663 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations

Gulfstream Aerospace Corporation Model GV and GV–SP airplanes. This AD was prompted by a new revision to the Airworthiness Limitations Section (ALS) of the Aircraft Maintenance Manual (AMM) based on fatigue and damage tolerance testing, and updated analysis. This AD requires revising the maintenance or inspection program to incorporate updated inspection requirements and life limits that address fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of PSEs is detected and corrected; such fatigue cracking could result in reduced structural integrity of the PSEs and critical components.

**DATES :**  This AD is effective December 27, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 27, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone: 800–810–4853; fax: 912– 965–3520; email: pubs@gulfstream.com ; Internet: http://www.gulfstream.com/ product

_support/technical

_

pubs/pubs/ index.htm . You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet
at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–4223. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 4223; 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 (phone: 800–647–5527) is Docket 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 :**  Ronald Wissing, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5552; fax: 404–474–5606; email: ronald.wissing@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Gulfstream Aerospace Corporation Model GV and GV–SP airplanes. The NPRM published in the Federal Register on March 14, 2016 (81 FR 13301) (‘‘the NPRM’’). The NPRM was prompted by a new revision to the ALS of the AMM, Chapter 05–10–10, based on fatigue and damage tolerance testing, and updated analysis. The NPRM proposed to require revising the maintenance or inspection program to update inspection requirements and life limits that address fatigue cracking of principal structural elements (PSEs). We are issuing this AD to ensure that fatigue cracking of PSEs is detected and corrected; such fatigue cracking could result in reduced structural integrity of the PSEs and critical components.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Specify Referenced Document

Gulfstream requested that we revise the **SUMMARY** section and the Discussion section of the NPRM, and paragraph (e) of the proposed AD, to refer to the AMM, Chapter 05–10–10, which contains updated inspection requirements and life limits.

We agree with the request. We have revised the **SUMMARY** and Discussion sections of this final rule, and paragraph (e) of this AD accordingly.
Request To Remove Certain Language From the NPRM

Gulfstream requested that we revise the FAA’s Determination section of the NPRM, which states that the unsafe condition is likely to exist or develop ‘‘in other products of the same type design.’’ Gulfstream requested that we remove the quoted language, and pointed out that they believe the statement is irrelevant to the unsafe condition.

We disagree with the commenter’s request. Our phrasing is intentional. The finding that the condition is likely to exist or develop in other products of the same type design is necessary to ensure that the AD falls within the scope of 14 CFR part 39 (‘‘Airworthiness Directives’’.) (Specifically, see 14 CFR 39.5.) Additionally, the FAA’s Determination section of the NPRM is not restated in this final rule. We have not changed this AD regarding this issue. Request for Clarification of Certain Language From the NPRM

Gulfstream requested clarification regarding which ‘‘operator maintenance documents’’ require revision. Gulfstream did not provide any justification for its request.

We agree that clarification is necessary. Regardless of the maintenance program that an operator uses, this AD requires revising the applicable maintenance or inspection program documentation. The owner or operator is responsible for maintaining its fleet in an airworthy condition, including compliance with 14 CFR part 39. This final rule has not been changed in this regard. Request To Clarify Applicability

Gulfstream requested that we revise the ‘‘Differences Between This Proposed AD and the Service Information’’ section of the NPRM. Gulfstream pointed out that they believe the applicability is contradictory to Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015. Gulfstream also mentioned that it does not believe an operator would be able to log compliance with the proposed AD.

We agree to clarify. The applicability of this AD differs from the effectivity of Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015, which excludes airplanes on which certain supplemental type certificates (STCs) have been accomplished. Airplanes on which those STCs have been accomplished are included in the applicability of this AD because those airplanes could have inspections and limits that are applicable. If it is determined that an airplane with a listed STC cannot accomplish the requirements of this AD, the operator may request an alternative method of compliance (AMOC) in accordance with paragraph (i) of this AD.

Also, we do not agree with the statement in Gulfstream Document GV– GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015, indicating that airplanes with specific STCs installed should be excluded from the effectivity of Gulfstream Document GV–GER–9973, Summary of Changes to


### 83664 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations

the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015. We have not changed this AD in this regard.Request To Allow the Use of LaterApproved Service Information

Gulfstream requested that we revise Note 1 to paragraph (g) of the proposed AD. Gulfstream specifically requested adding language that would specify ‘‘or later FAA approved revision’’ to clarify operator compliance with the proposed AD.

We do not agree to revise Note 1 to paragraph (g) of this AD to allow use of ‘‘later FAA-approved revisions.’’ Note 1 to paragraph (g) of this AD specifies the AMM revisions specifically identified in Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015. This AD does not require any actions to be done in accordance with the AMM revisions specified in Note 1 to paragraph (g) of this AD. Additionally, we may not refer to any document that does not yet exist. However, we have revised Note 1 to paragraph (g) of this AD to clarify the intent of that note. Request To Verify the Contact Information for Gulfstream

Gulfstream requested that we verify the contact information used in the

**ADDRESSES** section and paragraph (k)(3) of this AD before publication. Gulfstream stated that its contact information and data storage location may change before the publication date of the final rule.

We have verified the contact information used in the **ADDRESSES** section of this final rule, and found that no change is necessary.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM.

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR part 51

We reviewed Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015. The service information describes inspection requirements and life limits that address fatigue cracking of the PSEs. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the

**ADDRESSES** section. Costs of Compliance

We estimate that this AD affects 392 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Revision of the maintenance or inspection

program. 1 work-hour × $85 per hour = $85 ................. $0 $85 $33,320

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

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),

(3) Will not affect intrastate aviation in Alaska, and

(4) 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. 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 adding the following new airworthiness directive (AD):
2016–22–04 Gulfstream Aerospace Corporation: Amendment 39–18693; Docket No. FAA–2016–4223; Directorate Identifier 2015–NM–108–AD.

(a) Effective Date

This AD is effective December 27, 2016.

(b) Affected ADs

None.
(c) Applicability

This AD applies to Gulfstream Aerospace Corporation Model GV airplanes, certificated in any category, serial numbers 501 through 693 inclusive and serial number 699; and Model GV–SP airplanes, certificated in any category, serial numbers 5001 through 5433 inclusive.


### 83665 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations

(d) Subject

Air Transport Association (ATA) of America Code 32, Landing Gear; 53, Fuselage; 54, Nacelles/Pylons; 55, Stabilizers; and 57, Wings.

(e) Unsafe Condition

This AD was prompted by a new revision to the Airworthiness Limitations Section (ALS) of the Aircraft Maintenance Manual (AMM), Chapter 05–10–10, based on fatigue and damage tolerance testing, and updated analysis. We are issuing this AD to ensure fatigue cracking of principal structural elements (PSEs) is detected and corrected; such fatigue cracking could result in reduced structural integrity of the PSEs and critical components. (f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Revise Maintenance or Inspection Program

Within 12 months after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the airworthiness limitations specified in Gulfstream Document GV–GER– 9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015. The initial compliance times for the tasks identified in Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015, are at the applicable times specified in Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015, or within twelve months after the effective date of this AD, whichever occurs later.

Note 1 to paragraph (g) of this AD: Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015, specifies the following AMM revisions as additional sources of guidance for the actions required by paragraph (g) of this AD. For Model GV airplanes, AMM Revision 43, dated February 15, 2015; and for Model GV–SP airplanes, G500 or G550 AMM Revision 24, dated February 15, 2015, as applicable.

(h) No Alternative Actions or Intervals

After the maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions ( e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (i) of this AD. (i) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Atlanta Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j) of this AD.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.
(j) Related Information

For more information about this AD, contact Ronald Wissing, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5552; fax: 404– 474–5606; email: ronald.wissing@faa.gov.
(k) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Gulfstream Document GV–GER–9973, Summary of Changes to the GV Series Airworthiness Limitations, Revision C, dated January 8, 2015. The revision level and date of this document are not specified on the title page of the document.

(ii) Reserved. (3) For Gulfstream Aerospace Corporation service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone: 800– 810–4853; fax: 912–965–3520; email: pubs@ gulfstream.com; Internet: http:// www.gulfstream.com/product

_support/ technical

_ pubs/pubs/index.htm. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA 98057–3356. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this service information that is incorporated by reference 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 October
14, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–25743 Filed 11–21–16; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–6672; Directorate Identifier 2016–NM–022–AD; Amendment**  **39–18706; AD 2016–22–17]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This AD was prompted by a report that the grounding jumpers between the environmental control system (ECS) bracket and the current return network (CRN) straps near certain passenger entry doors were not bonded correctly during manufacturing. This AD requires changing the configuration of the grounding jumpers connecting the ECS brackets and CRN straps; measuring the bond resistance; and doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.

**DATES :**  This AD is effective December 27, 2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 27, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–
6672. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 6672; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday,